diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0240.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0240.dat new file mode 100644 index 00000000..94b36abc --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0240.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0240 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0240_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180 0.0000 0.0100 -1 + -170 0.3120 0.0100 -1 + -160 0.6240 0.0706 -1 + -150 0.9360 0.2428 -1 + -140 0.7699 0.4549 -1 + -130 0.6312 0.6818 -1 + -120 0.4861 0.8973 -1 + -110 0.3275 1.0763 -1 + -100 0.1610 1.1983 -1 + -90 0.0000 1.2500 -1 + -80 -0.1610 1.1983 -1 + -70 -0.3275 1.0763 -1 + -60 -0.4861 0.8973 -1 + -50 -0.6312 0.6818 -1 + -40 -0.7699 0.4549 -1 + -30 -0.9360 0.2428 -1 + -20 -0.6782 0.1306 -1 + -10 -0.6006 0.0183 -2.3658 + -9 -0.5703 0.0150 -2.1354 + -8 -0.5401 0.0124 -1.9128 + -7 -0.4863 0.0111 -1.6564 + -6 -0.3911 0.0101 -1.4075 + -5 -0.2829 0.0093 -1.2098 + -4 -0.1699 0.0086 -1.0246 + -3 -0.0547 0.0076 -0.9055 + -2 0.0671 0.0074 -0.9047 + -1 0.1884 0.0073 -0.9888 + 0 0.3092 0.0074 -1.0777 + 1 0.4307 0.0074 -1.1694 + 2 0.5503 0.0076 -1.2608 + 3 0.6677 0.0078 -1.3557 + 4 0.7807 0.0082 -1.4512 + 5 0.8921 0.0086 -1.5561 + 6 0.9830 0.0097 -1.6648 + 7 1.0196 0.0114 -1.7468 + 8 1.0527 0.0137 -1.8733 + 9 1.0932 0.0166 -2.0257 + 10 1.1352 0.0200 -2.1849 + 11 1.1432 0.0259 -2.3027 + 12 1.1730 0.0313 -2.5537 + 13 1.1826 0.0392 -2.7674 + 14 1.2087 0.0464 -3.0323 + 15 1.2272 0.0550 -3.2908 + 16 1.2557 0.0634 -3.5959 + 17 1.2806 0.0725 -3.9100 + 18 1.3037 0.0825 -4.2419 + 19 1.3252 0.0930 -4.5743 + 20 1.3439 0.1043 -4.9173 + 21 1.3613 0.1159 -5.2685 + 22 1.3809 0.1271 -5.6456 + 23 1.3894 0.1401 -5.9876 + 24 1.3961 0.1532 -6.3248 + 25 1.3970 0.1669 -6.6429 + 26 1.3922 0.1814 -6.9151 + 28 1.3673 0.2112 -7.3108 + 29 1.3488 0.2278 -7.4112 + 30 1.3371 0.2428 -7.5348 + 40 1.0999 0.4549 -1 + 50 0.9017 0.6818 -1 + 60 0.6944 0.8973 -1 + 70 0.4678 1.0763 -1 + 80 0.2300 1.1983 -1 + 90 0.0000 1.2500 -1 + 100 -0.1610 1.1983 -1 + 110 -0.3275 1.0763 -1 + 120 -0.4861 0.8973 -1 + 130 -0.6312 0.6818 -1 + 140 -0.7699 0.4549 -1 + 150 -0.9360 0.2428 -1 + 160 -0.6240 0.0706 -1 + 170 -0.3120 0.0100 -1 + 180 0.0000 0.0100 -1 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180 0.0000 0.0100 -1 + -170 0.3270 0.0100 -1 + -160 0.6541 0.0587 -1 + -150 0.9811 0.2318 -1 + -140 0.7974 0.4451 -1 + -130 0.6474 0.6736 -1 + -120 0.4948 0.8909 -1 + -110 0.3312 1.0719 -1 + -100 0.1619 1.1961 -1 + -90 0.0000 1.2500 -1 + -80 -0.1619 1.1961 -1 + -70 -0.3312 1.0719 -1 + -60 -0.4948 0.8909 -1 + -50 -0.6474 0.6736 -1 + -40 -0.7974 0.4451 -1 + -30 -0.9811 0.2318 -1 + -20 -0.7169 0.1237 -1 + -10 -0.6467 0.0156 -2.4629 + -9 -0.5996 0.0132 -2.1912 + -8 -0.5801 0.0111 -1.9816 + -7 -0.4950 0.0100 -1.6720 + -6 -0.3910 0.0092 -1.4078 + -5 -0.2810 0.0085 -1.2080 + -4 -0.1639 0.0080 -1.0184 + -3 -0.0454 0.0073 -0.8991 + -1 0.1982 0.0065 -0.9945 + 0 0.3213 0.0064 -1.0853 + 1 0.4423 0.0066 -1.1768 + 2 0.5645 0.0066 -1.2701 + 5 0.8977 0.0083 -1.5589 + 6 0.9769 0.0097 -1.6615 + 7 1.0311 0.0109 -1.7560 + 9 1.1327 0.0147 -2.0745 + 10 1.1526 0.0188 -2.2074 + 11 1.1873 0.0230 -2.3877 + 12 1.2028 0.0291 -2.6164 + 13 1.2313 0.0351 -2.8768 + 14 1.2601 0.0417 -3.1622 + 15 1.2941 0.0485 -3.4718 + 16 1.3216 0.0564 -3.7920 + 17 1.3498 0.0647 -4.1401 + 18 1.3733 0.0740 -4.4868 + 19 1.3966 0.0838 -4.8430 + 20 1.4115 0.0951 -5.1959 + 21 1.4270 0.1066 -5.5559 + 22 1.4404 0.1187 -5.9301 + 23 1.4449 0.1319 -6.2704 + 24 1.4587 0.1437 -6.6837 + 25 1.4594 0.1573 -7.0264 + 26 1.4601 0.1706 -7.3616 + 27 1.4562 0.1845 -7.6585 + 28 1.4482 0.1989 -7.9116 + 29 1.4181 0.2163 -7.9793 + 30 1.4016 0.2318 -8.1104 + 40 1.1391 0.4451 -1 + 50 0.9249 0.6736 -1 + 60 0.7068 0.8909 -1 + 70 0.4731 1.0719 -1 + 80 0.2313 1.1961 -1 + 90 0.0000 1.2500 -1 + 100 -0.1619 1.1961 -1 + 110 -0.3312 1.0719 -1 + 120 -0.4948 0.8909 -1 + 130 -0.6474 0.6736 -1 + 140 -0.7974 0.4451 -1 + 150 -0.9811 0.2318 -1 + 160 -0.6541 0.0587 -1 + 170 -0.3270 0.0100 -1 + 180 0.0000 0.0100 -1 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180 0.0000 0.0100 -1 + -170 0.3392 0.0100 -1 + -160 0.6784 0.0496 -1 + -150 1.0176 0.2235 -1 + -140 0.8196 0.4377 -1 + -130 0.6605 0.6674 -1 + -120 0.5018 0.8861 -1 + -110 0.3342 1.0686 -1 + -100 0.1627 1.1945 -1 + -90 0.0000 1.2500 -1 + -80 -0.1627 1.1945 -1 + -70 -0.3342 1.0686 -1 + -60 -0.5018 0.8861 -1 + -50 -0.6605 0.6674 -1 + -40 -0.8196 0.4377 -1 + -30 -1.0176 0.2235 -1 + -20 -0.7445 0.1188 -1 + -10 -0.6733 0.0141 -2.5188 + -9 -0.6311 0.0119 -2.2492 + -8 -0.5908 0.0105 -2.0003 + -7 -0.4967 0.0096 -1.6748 + -6 -0.3927 0.0088 -1.4104 + -5 -0.2789 0.0081 -1.2057 + -4 -0.1611 0.0077 -1.0152 + -3 -0.0419 0.0072 -0.8970 + -2 0.0793 0.0064 -0.9117 + -1 0.2025 0.0061 -0.9971 + 0 0.3254 0.0061 -1.0876 + 1 0.4490 0.0061 -1.1811 + 2 0.5682 0.0064 -1.2727 + 4 0.7966 0.0073 -1.4660 + 5 0.8946 0.0084 -1.5586 + 6 0.9801 0.0096 -1.6568 + 7 1.0446 0.0105 -1.7694 + 8 1.1065 0.0117 -1.9317 + 9 1.1411 0.0142 -2.0844 + 10 1.1776 0.0175 -2.2415 + 11 1.2014 0.0220 -2.4154 + 12 1.2315 0.0270 -2.6770 + 13 1.2585 0.0329 -2.9389 + 14 1.2967 0.0387 -3.2543 + 15 1.3269 0.0455 -3.5636 + 16 1.3566 0.0529 -3.8959 + 17 1.3838 0.0611 -4.2519 + 19 1.4278 0.0800 -4.9627 + 20 1.4607 0.0886 -5.3962 + 21 1.4730 0.1002 -5.7535 + 22 1.4807 0.1128 -6.1201 + 23 1.4853 0.1259 -6.4786 + 24 1.4917 0.1388 -6.8685 + 25 1.4944 0.1520 -7.2354 + 26 1.4918 0.1657 -7.5648 + 27 1.4848 0.1800 -7.8540 + 28 1.4765 0.1943 -8.1190 + 29 1.4665 0.2087 -8.3538 + 30 1.4537 0.2235 -8.5446 + 40 1.1708 0.4377 -1 + 50 0.9436 0.6674 -1 + 60 0.7169 0.8861 -1 + 70 0.4775 1.0686 -1 + 80 0.2324 1.1945 -1 + 90 0.0000 1.2500 -1 + 100 -0.1627 1.1945 -1 + 110 -0.3342 1.0686 -1 + 120 -0.5018 0.8861 -1 + 130 -0.6605 0.6674 -1 + 140 -0.8196 0.4377 -1 + 150 -1.0176 0.2235 -1 + 160 -0.6784 0.0496 -1 + 170 -0.3392 0.0100 -1 + 180 0.0000 0.0100 -1 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180 0.0000 0.0100 -1 + -170 0.4065 0.0100 -1 + -160 0.8130 0.0656 -1 + -150 0.9585 0.2382 -1 + -140 0.7836 0.4508 -1 + -130 0.6393 0.6784 -1 + -120 0.4904 0.8946 -1 + -110 0.3293 1.0744 -1 + -100 0.1615 1.1974 -1 + -90 0.0000 1.2500 -1 + -80 -0.1615 1.1974 -1 + -70 -0.3293 1.0744 -1 + -60 -0.4904 0.8946 -1 + -50 -0.6393 0.6784 -1 + -40 -0.7836 0.4508 -1 + -30 -0.9585 0.2382 -1 + -20 -0.8400 0.1070 -1 + -10 -0.6835 0.0136 -2.5481 + -9 -0.6551 0.0110 -2.2945 + -8 -0.5990 0.0100 -2.0149 + -5 -0.2785 0.0079 -1.2051 + -4 -0.1605 0.0074 -1.0146 + -3 -0.0396 0.0070 -0.8858 + -2 0.0815 0.0064 -0.9130 + -1 0.2046 0.0060 -0.9981 + 0 0.3288 0.0059 -1.0898 + 1 0.4505 0.0059 -1.1819 + 2 0.5696 0.0062 -1.2742 + 3 0.6869 0.0066 -1.3692 + 4 0.7958 0.0074 -1.4563 + 6 0.9864 0.0094 -1.6557 + 7 1.0636 0.0101 -1.7862 + 8 1.1217 0.0112 -1.9495 + 9 1.1532 0.0137 -2.0998 + 11 1.2140 0.0213 -2.4399 + 12 1.2522 0.0256 -2.7207 + 13 1.2922 0.0304 -3.0194 + 15 1.3624 0.0423 -3.6630 + 16 1.3922 0.0494 -4.0053 + 17 1.4225 0.0570 -4.3795 + 18 1.4431 0.0660 -4.7296 + 19 1.4663 0.0753 -5.1108 + 20 1.4819 0.0860 -5.4818 + 22 1.4994 0.1103 -6.2066 + 25 1.5113 0.1495 -7.3351 + 26 1.5098 0.1631 -7.6774 + 30 1.3693 0.2382 -6.1797 + 40 1.1195 0.4508 -1 + 50 0.9133 0.6784 -1 + 60 0.7006 0.8946 -1 + 70 0.4705 1.0744 -1 + 80 0.2307 1.1974 -1 + 90 0.0000 1.2500 -1 + 100 -0.1615 1.1974 -1 + 110 -0.3293 1.0744 -1 + 120 -0.4904 0.8946 -1 + 130 -0.6393 0.6784 -1 + 140 -0.7836 0.4508 -1 + 150 -0.9585 0.2382 -1 + 160 -0.8130 0.0656 -1 + 170 -0.4065 0.0100 -1 + 180 0.0000 0.0100 -1 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180 0.0000 0.0100 -1 + -170 0.3508 0.0100 -1 + -160 0.7017 0.0400 -1 + -150 1.0525 0.2147 -1 + -140 0.8408 0.4299 -1 + -130 0.6731 0.6609 -1 + -120 0.5085 0.8810 -1 + -110 0.3371 1.0651 -1 + -100 0.1634 1.1927 -1 + -90 0.0000 1.2500 -1 + -80 -0.1634 1.1927 -1 + -70 -0.3371 1.0651 -1 + -60 -0.5085 0.8810 -1 + -50 -0.6731 0.6609 -1 + -40 -0.8408 0.4299 -1 + -30 -1.0525 0.2147 -1 + -20 -0.7646 0.1141 -1 + -10 -0.6811 0.0135 -2.5243 + -9 -0.6851 0.0106 -2.3544 + -8 -0.6061 0.0097 -2.0276 + -6 -0.3941 0.0082 -1.4146 + -4 -0.1596 0.0072 -1.0137 + -3 -0.0388 0.0069 -0.8871 + -2 0.0830 0.0064 -0.9138 + -1 0.2067 0.0059 -0.9994 + 0 0.3302 0.0058 -1.0906 + 1 0.4512 0.0059 -1.1825 + 2 0.5700 0.0062 -1.2762 + 4 0.7938 0.0075 -1.4517 + 5 0.8930 0.0085 -1.5475 + 6 0.9896 0.0093 -1.6620 + 7 1.0843 0.0099 -1.8045 + 8 1.1285 0.0111 -1.9571 + 9 1.1695 0.0131 -2.1205 + 10 1.1873 0.0169 -2.2387 + 11 1.2351 0.0201 -2.4820 + 12 1.2707 0.0244 -2.7598 + 13 1.3094 0.0292 -3.0601 + 14 1.3479 0.0345 -3.3831 + 16 1.4132 0.0475 -4.0705 + 17 1.4381 0.0554 -4.4302 + 18 1.4631 0.0639 -4.7988 + 19 1.4825 0.0734 -5.1723 + 20 1.4971 0.0841 -5.5428 + 21 1.5047 0.0960 -5.8916 + 24 1.5435 0.1310 -7.1532 + 25 1.5472 0.1439 -7.5449 + 26 1.5476 0.1572 -7.9128 + 27 1.5436 0.1707 -8.246 + 28 1.5338 0.1849 -8.5292 + 29 1.5197 0.1997 -8.7629 + 30 1.5036 0.2147 -8.9588 + 40 1.2012 0.4299 -1 + 50 0.9615 0.6609 -1 + 60 0.7265 0.8810 -1 + 70 0.4816 1.0651 -1 + 80 0.2334 1.1927 -1 + 90 0.0000 1.2500 -1 + 100 -0.1634 1.1927 -1 + 110 -0.3371 1.0651 -1 + 120 -0.5085 0.8810 -1 + 130 -0.6731 0.6609 -1 + 140 -0.8408 0.4299 -1 + 150 -1.0525 0.2147 -1 + 160 -0.7017 0.0400 -1 + 170 -0.3508 0.0100 -1 + 180 0.0000 0.0100 -1 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180 0.0000 0.0100 -1 + -170 0.3695 0.0100 -1 + -160 0.7389 0.0433 -1 + -150 1.0447 0.2176 -1 + -140 0.8361 0.4326 -1 + -130 0.6703 0.6631 -1 + -120 0.5070 0.8827 -1 + -110 0.3365 1.0663 -1 + -100 0.1632 1.1933 -1 + -90 0.0000 1.2500 -1 + -80 -0.1632 1.1933 -1 + -70 -0.3365 1.0663 -1 + -60 -0.5070 0.8827 -1 + -50 -0.6703 0.6631 -1 + -40 -0.8361 0.4326 -1 + -30 -1.0447 0.2176 -1 + -20 -0.7942 0.1103 -1 + -10 -0.6944 0.0129 -2.5538 + -7 -0.5051 0.0088 -1.6890 + -6 -0.3931 0.0082 -1.4033 + -5 -0.2781 0.0075 -1.2051 + -4 -0.1595 0.0071 -1.0133 + -3 -0.0379 0.0068 -0.8899 + -2 0.0846 0.0064 -0.9146 + -1 0.2078 0.0058 -1.0002 + 0 0.3310 0.0058 -1.0908 + 1 0.4519 0.0058 -1.1833 + 2 0.5708 0.0061 -1.2722 + 3 0.6863 0.0066 -1.3593 + 4 0.7943 0.0074 -1.4554 + 5 0.8937 0.0084 -1.5503 + 6 0.9965 0.0090 -1.6685 + 7 1.0919 0.0097 -1.8120 + 8 1.1354 0.0109 -1.9652 + 10 1.2027 0.0161 -2.2646 + 11 1.2478 0.0194 -2.5076 + 12 1.2911 0.0232 -2.8034 + 13 1.3319 0.0276 -3.1135 + 14 1.3618 0.0335 -3.4179 + 15 1.3958 0.0395 -3.7559 + 17 1.4529 0.0540 -4.4787 + 18 1.4764 0.0625 -4.8444 + 19 1.4956 0.0720 -5.2221 + 20 1.5053 0.0831 -5.5750 + 22 1.5459 0.1037 -6.4227 + 23 1.5538 0.1161 -6.8324 + 24 1.5595 0.1287 -7.2408 + 25 1.5622 0.1418 -7.6314 + 26 1.5612 0.1552 -7.9964 + 27 1.5539 0.1691 -8.3139 + 28 1.5433 0.1835 -8.595 + 29 1.5306 0.1980 -8.8443 + 30 1.4925 0.2176 -8.363771554 + 40 1.1944 0.4326 -1 + 50 0.9575 0.6631 -1 + 60 0.7243 0.8827 -1 + 70 0.4807 1.0663 -1 + 80 0.2332 1.1933 -1 + 90 0.0000 1.2500 -1 + 100 -0.1632 1.1933 -1 + 110 -0.3365 1.0663 -1 + 120 -0.5070 0.8827 -1 + 130 -0.6703 0.6631 -1 + 140 -0.8361 0.4326 -1 + 150 -1.0447 0.2176 -1 + 160 -0.7389 0.0433 -1 + 170 -0.3695 0.0100 -1 + 180 0.0000 0.0100 -1 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180 0.0000 0.0100 -1 + -170 0.3561 0.0100 -1 + -160 0.7121 0.0361 -1 + -150 1.0682 0.2110 -1 + -140 0.8504 0.4267 -1 + -130 0.6787 0.6582 -1 + -120 0.5115 0.8789 -1 + -110 0.3384 1.0637 -1 + -100 0.1637 1.1919 -1 + -90 0.0000 1.2500 -1 + -80 -0.1637 1.1919 -1 + -70 -0.3384 1.0637 -1 + -60 -0.5115 0.8789 -1 + -50 -0.6787 0.6582 -1 + -40 -0.8504 0.4267 -1 + -30 -1.0682 0.2110 -1 + -20 -0.7818 0.1117 -1 + -10 -0.7078 0.0124 -2.5820 + -9 -0.6882 0.0105 -2.3471 + -8 -0.6127 0.0092 -2.0403 + -6 -0.3930 0.0081 -1.4009 + -5 -0.2780 0.0074 -1.2048 + -4 -0.1594 0.0069 -1.0132 + -3 -0.0371 0.0067 -0.8903 + -2 0.0857 0.0063 -0.9153 + -1 0.2083 0.0058 -1.0004 + 0 0.3320 0.0057 -1.0916 + 1 0.4508 0.0059 -1.1835 + 2 0.5707 0.0061 -1.2714 + 3 0.6849 0.0067 -1.3575 + 5 0.8968 0.0083 -1.5536 + 6 0.9995 0.0090 -1.6719 + 7 1.0994 0.0095 -1.8194 + 8 1.1396 0.0107 -1.9697 + 11 1.2595 0.0188 -2.5308 + 12 1.3027 0.0225 -2.8278 + 14 1.3829 0.0318 -3.4708 + 16 1.4381 0.0453 -4.1475 + 18 1.4876 0.0613 -4.8828 + 21 1.5477 0.0904 -6.0795 + 22 1.5578 0.1021 -6.4768 + 23 1.5668 0.1143 -6.8990 + 24 1.5715 0.1270 -7.3058 + 25 1.5731 0.1402 -7.6939 + 26 1.5686 0.1540 -8.0423 + 27 1.5615 0.1680 -8.3631 + 28 1.5521 0.1821 -8.6566 + 29 1.5406 0.1964 -8.9183 + 30 1.5260 0.2110 -9.1387 + 40 1.2148 0.4267 -1 + 50 0.9696 0.6582 -1 + 60 0.7308 0.8789 -1 + 70 0.4835 1.0637 -1 + 80 0.2339 1.1919 -1 + 90 0.0000 1.2500 -1 + 100 -0.1637 1.1919 -1 + 110 -0.3384 1.0637 -1 + 120 -0.5115 0.8789 -1 + 130 -0.6787 0.6582 -1 + 140 -0.8504 0.4267 -1 + 150 -1.0682 0.2110 -1 + 160 -0.7121 0.0361 -1 + 170 -0.3561 0.0100 -1 + 180 0.0000 0.0100 -1 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0240_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0240_coords.txt new file mode 100644 index 00000000..99568655 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0240_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0240 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.001740 0.009990 + 0.009990 0.025540 + 0.026840 0.043840 + 0.085380 0.081830 + 0.126020 0.098890 + 0.173070 0.113700 + 0.225630 0.125450 + 0.343100 0.136890 + 0.405650 0.135010 + 0.469030 0.128320 + 0.532130 0.117850 + 0.653880 0.089820 + 0.711010 0.074320 + 0.764750 0.059150 + 0.814500 0.045100 + 0.899560 0.022380 + 0.933650 0.014140 + 0.961390 0.007980 + 0.982280 0.002440 + 0.982280 0.001830 + 0.961390 0.002090 + 0.933510 0.000850 + 0.859090 -0.008040 + 0.813820 -0.016050 + 0.764090 -0.026350 + 0.710600 -0.038510 + 0.594970 -0.065500 + 0.534160 -0.078430 + 0.472340 -0.089680 + 0.410300 -0.098140 + 0.289530 -0.102840 + 0.233070 -0.098960 + 0.180640 -0.091900 + 0.133180 -0.082080 + 0.056790 -0.055970 + 0.029750 -0.040380 + 0.011270 -0.024430 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0247.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0247.dat new file mode 100644 index 00000000..116e81c9 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0247.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0247 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0247_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0127 -1.0184 + -170.000 0.3091 0.0127 -1.0184 + -160.000 0.6183 0.0727 -1.0184 + -150.000 0.9274 0.2433 -1.0184 + -140.000 0.7628 0.4535 -1.0184 + -130.000 0.6254 0.6783 -1.0184 + -120.000 0.4816 0.8918 -1.0184 + -110.000 0.3245 1.0691 -1.0184 + -100.000 0.1595 1.1900 -1.0184 + -90.000 0.0000 1.2413 -1.0184 + -80.000 -0.1595 1.1900 -1.0184 + -70.000 -0.3245 1.0691 -1.0184 + -60.000 -0.4816 0.8918 -1.0184 + -50.000 -0.6254 0.6783 -1.0184 + -40.000 -0.7628 0.4535 -1.0184 + -30.000 -0.9274 0.2433 -1.0184 + -20.000 -0.6720 0.1322 -1.0184 + -10.000 -0.5951 0.0209 -2.3716 + -9.000 -0.5650 0.0176 -2.1434 + -8.000 -0.5351 0.0150 -1.9228 + -7.000 -0.4818 0.0138 -1.6688 + -6.000 -0.3875 0.0128 -1.4222 + -5.000 -0.2803 0.0120 -1.2263 + -4.000 -0.1683 0.0113 -1.0428 + -3.000 -0.0542 0.0103 -0.9248 + -2.000 0.0665 0.0101 -0.9240 + -1.000 0.1867 0.0100 -1.0073 + 0.000 0.3064 0.0101 -1.0954 + 1.000 0.4267 0.0101 -1.1863 + 2.000 0.5452 0.0103 -1.2768 + 3.000 0.6616 0.0105 -1.3708 + 4.000 0.7735 0.0109 -1.4655 + 5.000 0.8839 0.0113 -1.5694 + 6.000 0.9739 0.0124 -1.6771 + 7.000 1.0102 0.0141 -1.7583 + 8.000 1.0430 0.0163 -1.8837 + 9.000 1.0831 0.0192 -2.0347 + 10.000 1.1247 0.0226 -2.1924 + 11.000 1.1327 0.0284 -2.3091 + 12.000 1.1622 0.0338 -2.5578 + 13.000 1.1717 0.0416 -2.7695 + 14.000 1.1976 0.0487 -3.0320 + 15.000 1.2159 0.0573 -3.2881 + 16.000 1.2441 0.0656 -3.5904 + 17.000 1.2688 0.0746 -3.9016 + 18.000 1.2917 0.0845 -4.2305 + 19.000 1.3130 0.0949 -4.5598 + 20.000 1.3315 0.1061 -4.8996 + 21.000 1.3488 0.1176 -5.2476 + 22.000 1.3682 0.1287 -5.6212 + 23.000 1.3766 0.1416 -5.9601 + 24.000 1.3832 0.1546 -6.2942 + 25.000 1.3841 0.1681 -6.6093 + 26.000 1.3794 0.1825 -6.8790 + 28.000 1.3547 0.2120 -7.2711 + 29.000 1.3364 0.2285 -7.3706 + 30.000 1.3248 0.2433 -7.4930 + 40.000 1.0898 0.4535 -1.0184 + 50.000 0.8934 0.6783 -1.0184 + 60.000 0.6880 0.8918 -1.0184 + 70.000 0.4635 1.0691 -1.0184 + 80.000 0.2279 1.1900 -1.0184 + 90.000 0.0000 1.2413 -1.0184 + 100.000 -0.1595 1.1900 -1.0184 + 110.000 -0.3245 1.0691 -1.0184 + 120.000 -0.4816 0.8918 -1.0184 + 130.000 -0.6254 0.6783 -1.0184 + 140.000 -0.7628 0.4535 -1.0184 + 150.000 -0.9274 0.2433 -1.0184 + 160.000 -0.6183 0.0727 -1.0184 + 170.000 -0.3091 0.0127 -1.0184 + 180.000 0.0000 0.0127 -1.0184 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0161 -1.0184 + -170.000 0.3240 0.0161 -1.0184 + -160.000 0.6481 0.0643 -1.0184 + -150.000 0.9721 0.2358 -1.0184 + -140.000 0.7901 0.4472 -1.0184 + -130.000 0.6414 0.6736 -1.0184 + -120.000 0.4902 0.8889 -1.0184 + -110.000 0.3281 1.0682 -1.0184 + -100.000 0.1604 1.1913 -1.0184 + -90.000 0.0000 1.2447 -1.0184 + -80.000 -0.1604 1.1913 -1.0184 + -70.000 -0.3281 1.0682 -1.0184 + -60.000 -0.4902 0.8889 -1.0184 + -50.000 -0.6414 0.6736 -1.0184 + -40.000 -0.7901 0.4472 -1.0184 + -30.000 -0.9721 0.2358 -1.0184 + -20.000 -0.7103 0.1287 -1.0184 + -10.000 -0.6407 0.0216 -2.4678 + -9.000 -0.5941 0.0192 -2.1986 + -8.000 -0.5748 0.0172 -1.9910 + -7.000 -0.4904 0.0161 -1.6842 + -6.000 -0.3874 0.0153 -1.4225 + -5.000 -0.2784 0.0146 -1.2245 + -4.000 -0.1624 0.0141 -1.0367 + -3.000 -0.0450 0.0134 -0.9185 + -1.000 0.1964 0.0126 -1.0130 + 0.000 0.3183 0.0125 -1.1029 + 1.000 0.4382 0.0127 -1.1936 + 2.000 0.5593 0.0127 -1.2860 + 5.000 0.8894 0.0144 -1.5722 + 6.000 0.9679 0.0158 -1.6738 + 7.000 1.0216 0.0170 -1.7675 + 9.000 1.1223 0.0207 -2.0830 + 10.000 1.1420 0.0248 -2.2147 + 11.000 1.1764 0.0290 -2.3933 + 12.000 1.1917 0.0350 -2.6199 + 13.000 1.2200 0.0409 -2.8779 + 14.000 1.2485 0.0475 -3.1607 + 15.000 1.2822 0.0542 -3.4675 + 16.000 1.3094 0.0621 -3.7847 + 17.000 1.3374 0.0703 -4.1296 + 18.000 1.3607 0.0795 -4.4731 + 19.000 1.3837 0.0892 -4.8260 + 20.000 1.3985 0.1004 -5.1757 + 21.000 1.4139 0.1118 -5.5324 + 22.000 1.4271 0.1238 -5.9031 + 23.000 1.4316 0.1369 -6.2403 + 24.000 1.4453 0.1485 -6.6498 + 25.000 1.4460 0.1620 -6.9893 + 26.000 1.4467 0.1752 -7.3214 + 27.000 1.4428 0.1890 -7.6156 + 28.000 1.4349 0.2032 -7.8664 + 29.000 1.4050 0.2205 -7.9334 + 30.000 1.3887 0.2358 -8.0633 + 40.000 1.1286 0.4472 -1.0184 + 50.000 0.9164 0.6736 -1.0184 + 60.000 0.7003 0.8889 -1.0184 + 70.000 0.4687 1.0682 -1.0184 + 80.000 0.2292 1.1913 -1.0184 + 90.000 0.0000 1.2447 -1.0184 + 100.000 -0.1604 1.1913 -1.0184 + 110.000 -0.3281 1.0682 -1.0184 + 120.000 -0.4902 0.8889 -1.0184 + 130.000 -0.6414 0.6736 -1.0184 + 140.000 -0.7901 0.4472 -1.0184 + 150.000 -0.9721 0.2358 -1.0184 + 160.000 -0.6481 0.0643 -1.0184 + 170.000 -0.3240 0.0161 -1.0184 + 180.000 0.0000 0.0161 -1.0184 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0164 -1.0184 + -170.000 0.3361 0.0164 -1.0184 + -160.000 0.6722 0.0556 -1.0184 + -150.000 1.0082 0.2279 -1.0184 + -140.000 0.8121 0.4401 -1.0184 + -130.000 0.6544 0.6677 -1.0184 + -120.000 0.4972 0.8844 -1.0184 + -110.000 0.3311 1.0652 -1.0184 + -100.000 0.1612 1.1899 -1.0184 + -90.000 0.0000 1.2449 -1.0184 + -80.000 -0.1612 1.1899 -1.0184 + -70.000 -0.3311 1.0652 -1.0184 + -60.000 -0.4972 0.8844 -1.0184 + -50.000 -0.6544 0.6677 -1.0184 + -40.000 -0.8121 0.4401 -1.0184 + -30.000 -1.0082 0.2279 -1.0184 + -20.000 -0.7376 0.1242 -1.0184 + -10.000 -0.6671 0.0204 -2.5232 + -9.000 -0.6253 0.0182 -2.2561 + -8.000 -0.5854 0.0169 -2.0095 + -7.000 -0.4921 0.0160 -1.6870 + -6.000 -0.3891 0.0152 -1.4250 + -5.000 -0.2763 0.0145 -1.2222 + -4.000 -0.1596 0.0141 -1.0335 + -3.000 -0.0415 0.0136 -0.9164 + -2.000 0.0786 0.0128 -0.9309 + -1.000 0.2006 0.0125 -1.0155 + 0.000 0.3224 0.0125 -1.1052 + 1.000 0.4449 0.0125 -1.1979 + 2.000 0.5630 0.0128 -1.2886 + 4.000 0.7893 0.0137 -1.4801 + 5.000 0.8864 0.0148 -1.5719 + 6.000 0.9711 0.0160 -1.6692 + 7.000 1.0350 0.0169 -1.7807 + 8.000 1.0963 0.0180 -1.9415 + 9.000 1.1306 0.0205 -2.0928 + 10.000 1.1668 0.0238 -2.2485 + 11.000 1.1903 0.0282 -2.4208 + 12.000 1.2202 0.0332 -2.6800 + 13.000 1.2469 0.0390 -2.9395 + 14.000 1.2848 0.0448 -3.2520 + 15.000 1.3147 0.0515 -3.5584 + 16.000 1.3441 0.0589 -3.8876 + 17.000 1.3711 0.0670 -4.2404 + 19.000 1.4146 0.0857 -4.9446 + 20.000 1.4472 0.0942 -5.3741 + 21.000 1.4594 0.1057 -5.7281 + 22.000 1.4671 0.1182 -6.0914 + 23.000 1.4716 0.1312 -6.4466 + 24.000 1.4780 0.1440 -6.8329 + 25.000 1.4806 0.1570 -7.1964 + 26.000 1.4781 0.1706 -7.5228 + 27.000 1.4711 0.1848 -7.8093 + 28.000 1.4629 0.1990 -8.0719 + 29.000 1.4530 0.2132 -8.3045 + 30.000 1.4403 0.2279 -8.4935 + 40.000 1.1600 0.4401 -1.0184 + 50.000 0.9349 0.6677 -1.0184 + 60.000 0.7103 0.8844 -1.0184 + 70.000 0.4731 1.0652 -1.0184 + 80.000 0.2303 1.1899 -1.0184 + 90.000 0.0000 1.2449 -1.0184 + 100.000 -0.1612 1.1899 -1.0184 + 110.000 -0.3311 1.0652 -1.0184 + 120.000 -0.4972 0.8844 -1.0184 + 130.000 -0.6544 0.6677 -1.0184 + 140.000 -0.8121 0.4401 -1.0184 + 150.000 -1.0082 0.2279 -1.0184 + 160.000 -0.6722 0.0556 -1.0184 + 170.000 -0.3361 0.0164 -1.0184 + 180.000 0.0000 0.0164 -1.0184 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0164 -1.0184 + -170.000 0.4028 0.0164 -1.0184 + -160.000 0.8055 0.0714 -1.0184 + -150.000 0.9497 0.2425 -1.0184 + -140.000 0.7764 0.4531 -1.0184 + -130.000 0.6334 0.6786 -1.0184 + -120.000 0.4859 0.8928 -1.0184 + -110.000 0.3263 1.0710 -1.0184 + -100.000 0.1600 1.1928 -1.0184 + -90.000 0.0000 1.2449 -1.0184 + -80.000 -0.1600 1.1928 -1.0184 + -70.000 -0.3263 1.0710 -1.0184 + -60.000 -0.4859 0.8928 -1.0184 + -50.000 -0.6334 0.6786 -1.0184 + -40.000 -0.7764 0.4531 -1.0184 + -30.000 -0.9497 0.2425 -1.0184 + -20.000 -0.8323 0.1125 -1.0184 + -10.000 -0.6772 0.0199 -2.5523 + -9.000 -0.6491 0.0173 -2.3010 + -8.000 -0.5935 0.0164 -2.0240 + -5.000 -0.2759 0.0143 -1.2216 + -4.000 -0.1590 0.0138 -1.0329 + -3.000 -0.0392 0.0134 -0.9053 + -2.000 0.0807 0.0128 -0.9322 + -1.000 0.2027 0.0124 -1.0165 + 0.000 0.3258 0.0123 -1.1074 + 1.000 0.4464 0.0123 -1.1986 + 2.000 0.5644 0.0126 -1.2901 + 3.000 0.6806 0.0130 -1.3842 + 4.000 0.7885 0.0138 -1.4705 + 6.000 0.9773 0.0158 -1.6681 + 7.000 1.0538 0.0165 -1.7974 + 8.000 1.1114 0.0175 -1.9592 + 9.000 1.1426 0.0200 -2.1081 + 11.000 1.2028 0.0276 -2.4451 + 12.000 1.2407 0.0318 -2.7233 + 13.000 1.2803 0.0366 -3.0192 + 15.000 1.3499 0.0484 -3.6569 + 16.000 1.3794 0.0554 -3.9960 + 17.000 1.4094 0.0629 -4.3668 + 18.000 1.4298 0.0718 -4.7137 + 19.000 1.4528 0.0811 -5.0914 + 20.000 1.4683 0.0917 -5.4589 + 22.000 1.4856 0.1157 -6.1771 + 25.000 1.4974 0.1546 -7.2952 + 26.000 1.4959 0.1680 -7.6343 + 30.000 1.3567 0.2425 -6.1504 + 40.000 1.1092 0.4531 -1.0184 + 50.000 0.9049 0.6786 -1.0184 + 60.000 0.6941 0.8928 -1.0184 + 70.000 0.4662 1.0710 -1.0184 + 80.000 0.2286 1.1928 -1.0184 + 90.000 0.0000 1.2449 -1.0184 + 100.000 -0.1600 1.1928 -1.0184 + 110.000 -0.3263 1.0710 -1.0184 + 120.000 -0.4859 0.8928 -1.0184 + 130.000 -0.6334 0.6786 -1.0184 + 140.000 -0.7764 0.4531 -1.0184 + 150.000 -0.9497 0.2425 -1.0184 + 160.000 -0.8055 0.0714 -1.0184 + 170.000 -0.4028 0.0164 -1.0184 + 180.000 0.0000 0.0164 -1.0184 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0164 -1.0184 + -170.000 0.3476 0.0164 -1.0184 + -160.000 0.6952 0.0461 -1.0184 + -150.000 1.0428 0.2192 -1.0184 + -140.000 0.8331 0.4324 -1.0184 + -130.000 0.6669 0.6613 -1.0184 + -120.000 0.5038 0.8793 -1.0184 + -110.000 0.3340 1.0617 -1.0184 + -100.000 0.1619 1.1882 -1.0184 + -90.000 0.0000 1.2449 -1.0184 + -80.000 -0.1619 1.1882 -1.0184 + -70.000 -0.3340 1.0617 -1.0184 + -60.000 -0.5038 0.8793 -1.0184 + -50.000 -0.6669 0.6613 -1.0184 + -40.000 -0.8331 0.4324 -1.0184 + -30.000 -1.0428 0.2192 -1.0184 + -20.000 -0.7576 0.1195 -1.0184 + -10.000 -0.6748 0.0198 -2.5287 + -9.000 -0.6788 0.0169 -2.3603 + -8.000 -0.6005 0.0161 -2.0366 + -6.000 -0.3905 0.0146 -1.4292 + -4.000 -0.1581 0.0136 -1.0320 + -3.000 -0.0384 0.0133 -0.9066 + -2.000 0.0822 0.0128 -0.9330 + -1.000 0.2048 0.0123 -1.0178 + 0.000 0.3272 0.0122 -1.1082 + 1.000 0.4470 0.0123 -1.1992 + 2.000 0.5647 0.0126 -1.2921 + 4.000 0.7865 0.0139 -1.4660 + 5.000 0.8848 0.0149 -1.5609 + 6.000 0.9805 0.0157 -1.6743 + 7.000 1.0743 0.0163 -1.8155 + 8.000 1.1181 0.0174 -1.9667 + 9.000 1.1587 0.0194 -2.1286 + 10.000 1.1764 0.0232 -2.2457 + 11.000 1.2237 0.0264 -2.4868 + 12.000 1.2590 0.0306 -2.7620 + 13.000 1.2973 0.0354 -3.0595 + 14.000 1.3355 0.0406 -3.3796 + 16.000 1.4002 0.0535 -4.0606 + 17.000 1.4249 0.0613 -4.4170 + 18.000 1.4496 0.0698 -4.7822 + 19.000 1.4688 0.0792 -5.1523 + 20.000 1.4833 0.0898 -5.5194 + 21.000 1.4908 0.1016 -5.8650 + 24.000 1.5293 0.1362 -7.1149 + 25.000 1.5329 0.1490 -7.5030 + 26.000 1.5333 0.1622 -7.8676 + 27.000 1.5294 0.1756 -8.1977 + 28.000 1.5197 0.1896 -8.4783 + 29.000 1.5057 0.2043 -8.7098 + 30.000 1.4898 0.2192 -8.9039 + 40.000 1.1901 0.4324 -1.0184 + 50.000 0.9526 0.6613 -1.0184 + 60.000 0.7198 0.8793 -1.0184 + 70.000 0.4772 1.0617 -1.0184 + 80.000 0.2313 1.1882 -1.0184 + 90.000 0.0000 1.2449 -1.0184 + 100.000 -0.1619 1.1882 -1.0184 + 110.000 -0.3340 1.0617 -1.0184 + 120.000 -0.5038 0.8793 -1.0184 + 130.000 -0.6669 0.6613 -1.0184 + 140.000 -0.8331 0.4324 -1.0184 + 150.000 -1.0428 0.2192 -1.0184 + 160.000 -0.6952 0.0461 -1.0184 + 170.000 -0.3476 0.0164 -1.0184 + 180.000 0.0000 0.0164 -1.0184 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0164 -1.0184 + -170.000 0.3661 0.0164 -1.0184 + -160.000 0.7321 0.0493 -1.0184 + -150.000 1.0351 0.2220 -1.0184 + -140.000 0.8284 0.4351 -1.0184 + -130.000 0.6641 0.6634 -1.0184 + -120.000 0.5023 0.8810 -1.0184 + -110.000 0.3334 1.0629 -1.0184 + -100.000 0.1617 1.1888 -1.0184 + -90.000 0.0000 1.2449 -1.0184 + -80.000 -0.1617 1.1888 -1.0184 + -70.000 -0.3334 1.0629 -1.0184 + -60.000 -0.5023 0.8810 -1.0184 + -50.000 -0.6641 0.6634 -1.0184 + -40.000 -0.8284 0.4351 -1.0184 + -30.000 -1.0351 0.2220 -1.0184 + -20.000 -0.7869 0.1157 -1.0184 + -10.000 -0.6880 0.0192 -2.5579 + -7.000 -0.5004 0.0152 -1.7011 + -6.000 -0.3895 0.0146 -1.4180 + -5.000 -0.2755 0.0139 -1.2216 + -4.000 -0.1580 0.0135 -1.0316 + -3.000 -0.0376 0.0132 -0.9093 + -2.000 0.0838 0.0128 -0.9338 + -1.000 0.2059 0.0122 -1.0186 + 0.000 0.3280 0.0122 -1.1084 + 1.000 0.4477 0.0122 -1.2000 + 2.000 0.5655 0.0125 -1.2881 + 3.000 0.6800 0.0130 -1.3744 + 4.000 0.7870 0.0138 -1.4696 + 5.000 0.8855 0.0148 -1.5637 + 6.000 0.9873 0.0154 -1.6808 + 7.000 1.0818 0.0161 -1.8229 + 8.000 1.1249 0.0172 -1.9747 + 10.000 1.1916 0.0224 -2.2714 + 11.000 1.2363 0.0257 -2.5121 + 12.000 1.2792 0.0294 -2.8052 + 13.000 1.3196 0.0338 -3.1125 + 14.000 1.3493 0.0396 -3.4141 + 15.000 1.3829 0.0456 -3.7489 + 17.000 1.4395 0.0600 -4.4651 + 18.000 1.4628 0.0684 -4.8274 + 19.000 1.4818 0.0778 -5.2016 + 20.000 1.4914 0.0888 -5.5513 + 22.000 1.5317 0.1092 -6.3912 + 23.000 1.5395 0.1215 -6.7971 + 24.000 1.5451 0.1340 -7.2017 + 25.000 1.5478 0.1469 -7.5887 + 26.000 1.5468 0.1602 -7.9504 + 27.000 1.5396 0.1740 -8.2650 + 28.000 1.5291 0.1883 -8.5435 + 29.000 1.5165 0.2026 -8.7905 + 30.000 1.4788 0.2220 -8.3144 + 40.000 1.1834 0.4351 -1.0184 + 50.000 0.9487 0.6634 -1.0184 + 60.000 0.7176 0.8810 -1.0184 + 70.000 0.4763 1.0629 -1.0184 + 80.000 0.2311 1.1888 -1.0184 + 90.000 0.0000 1.2449 -1.0184 + 100.000 -0.1617 1.1888 -1.0184 + 110.000 -0.3334 1.0629 -1.0184 + 120.000 -0.5023 0.8810 -1.0184 + 130.000 -0.6641 0.6634 -1.0184 + 140.000 -0.8284 0.4351 -1.0184 + 150.000 -1.0351 0.2220 -1.0184 + 160.000 -0.7321 0.0493 -1.0184 + 170.000 -0.3661 0.0164 -1.0184 + 180.000 0.0000 0.0164 -1.0184 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0164 -1.0184 + -170.000 0.3528 0.0164 -1.0184 + -160.000 0.7055 0.0422 -1.0184 + -150.000 1.0584 0.2155 -1.0184 + -140.000 0.8426 0.4292 -1.0184 + -130.000 0.6724 0.6586 -1.0184 + -120.000 0.5068 0.8773 -1.0184 + -110.000 0.3353 1.0604 -1.0184 + -100.000 0.1622 1.1874 -1.0184 + -90.000 0.0000 1.2449 -1.0184 + -80.000 -0.1622 1.1874 -1.0184 + -70.000 -0.3353 1.0604 -1.0184 + -60.000 -0.5068 0.8773 -1.0184 + -50.000 -0.6724 0.6586 -1.0184 + -40.000 -0.8426 0.4292 -1.0184 + -30.000 -1.0584 0.2155 -1.0184 + -20.000 -0.7746 0.1171 -1.0184 + -10.000 -0.7013 0.0187 -2.5858 + -9.000 -0.6819 0.0169 -2.3531 + -8.000 -0.6071 0.0156 -2.0491 + -6.000 -0.3894 0.0145 -1.4156 + -5.000 -0.2754 0.0138 -1.2213 + -4.000 -0.1579 0.0133 -1.0315 + -3.000 -0.0368 0.0131 -0.9097 + -2.000 0.0849 0.0127 -0.9345 + -1.000 0.2064 0.0122 -1.0188 + 0.000 0.3289 0.0121 -1.1092 + 1.000 0.4466 0.0123 -1.2002 + 2.000 0.5654 0.0125 -1.2873 + 3.000 0.6786 0.0131 -1.3726 + 5.000 0.8885 0.0147 -1.5669 + 6.000 0.9903 0.0154 -1.6841 + 7.000 1.0893 0.0159 -1.8303 + 8.000 1.1291 0.0170 -1.9792 + 11.000 1.2479 0.0251 -2.5351 + 12.000 1.2907 0.0287 -2.8294 + 14.000 1.3702 0.0380 -3.4665 + 16.000 1.4249 0.0513 -4.1369 + 18.000 1.4739 0.0672 -4.8655 + 21.000 1.5334 0.0960 -6.0511 + 22.000 1.5435 0.1076 -6.4448 + 23.000 1.5524 0.1197 -6.8631 + 24.000 1.5570 0.1323 -7.2661 + 25.000 1.5586 0.1454 -7.6507 + 26.000 1.5542 0.1590 -7.9959 + 27.000 1.5471 0.1729 -8.3137 + 28.000 1.5378 0.1869 -8.6045 + 29.000 1.5264 0.2010 -8.8638 + 30.000 1.5119 0.2155 -9.0822 + 40.000 1.2036 0.4292 -1.0184 + 50.000 0.9607 0.6586 -1.0184 + 60.000 0.7241 0.8773 -1.0184 + 70.000 0.4790 1.0604 -1.0184 + 80.000 0.2317 1.1874 -1.0184 + 90.000 0.0000 1.2449 -1.0184 + 100.000 -0.1622 1.1874 -1.0184 + 110.000 -0.3353 1.0604 -1.0184 + 120.000 -0.5068 0.8773 -1.0184 + 130.000 -0.6724 0.6586 -1.0184 + 140.000 -0.8426 0.4292 -1.0184 + 150.000 -1.0584 0.2155 -1.0184 + 160.000 -0.7055 0.0422 -1.0184 + 170.000 -0.3528 0.0164 -1.0184 + 180.000 0.0000 0.0164 -1.0184 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0247_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0247_coords.txt new file mode 100644 index 00000000..76becdc1 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0247_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0247 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.021573 + 0.027091 0.045571 + 0.060263 0.070519 + 0.105430 0.093593 + 0.161359 0.113695 + 0.226526 0.129332 + 0.299152 0.139084 + 0.377257 0.140958 + 0.458710 0.134375 + 0.541290 0.120926 + 0.622743 0.102688 + 0.700848 0.081979 + 0.773474 0.061268 + 0.838641 0.042604 + 0.894570 0.027238 + 0.939737 0.015604 + 0.972909 0.007552 + 0.993181 0.002511 + 1.000000 0.000000 + 0.993181 -0.000009 + 0.972909 0.000021 + 0.939737 -0.001786 + 0.894570 -0.006851 + 0.838641 -0.015998 + 0.773474 -0.029320 + 0.700848 -0.046093 + 0.622743 -0.064559 + 0.541290 -0.082348 + 0.458710 -0.096978 + 0.377257 -0.106009 + 0.299152 -0.107583 + 0.226526 -0.102345 + 0.161359 -0.091881 + 0.105430 -0.077436 + 0.060263 -0.059906 + 0.027091 -0.040088 + 0.006819 -0.019333 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0259.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0259.dat new file mode 100644 index 00000000..2122f139 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0259.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0259 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0259_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0173 -1.0500 + -170.000 0.3042 0.0173 -1.0500 + -160.000 0.6084 0.0763 -1.0500 + -150.000 0.9126 0.2442 -1.0500 + -140.000 0.7507 0.4510 -1.0500 + -130.000 0.6154 0.6723 -1.0500 + -120.000 0.4739 0.8824 -1.0500 + -110.000 0.3193 1.0569 -1.0500 + -100.000 0.1570 1.1758 -1.0500 + -90.000 0.0000 1.2263 -1.0500 + -80.000 -0.1570 1.1758 -1.0500 + -70.000 -0.3193 1.0569 -1.0500 + -60.000 -0.4739 0.8824 -1.0500 + -50.000 -0.6154 0.6723 -1.0500 + -40.000 -0.7507 0.4510 -1.0500 + -30.000 -0.9126 0.2442 -1.0500 + -20.000 -0.6612 0.1348 -1.0500 + -10.000 -0.5856 0.0253 -2.3817 + -9.000 -0.5560 0.0221 -2.1570 + -8.000 -0.5266 0.0196 -1.9400 + -7.000 -0.4741 0.0183 -1.6900 + -6.000 -0.3813 0.0173 -1.4473 + -5.000 -0.2758 0.0166 -1.2546 + -4.000 -0.1657 0.0159 -1.0740 + -3.000 -0.0533 0.0149 -0.9579 + -2.000 0.0654 0.0147 -0.9571 + -1.000 0.1837 0.0146 -1.0391 + 0.000 0.3015 0.0147 -1.1258 + 1.000 0.4199 0.0147 -1.2152 + 2.000 0.5365 0.0149 -1.3043 + 3.000 0.6510 0.0151 -1.3968 + 4.000 0.7612 0.0155 -1.4899 + 5.000 0.8698 0.0159 -1.5922 + 6.000 0.9584 0.0170 -1.6982 + 7.000 0.9941 0.0186 -1.7781 + 8.000 1.0264 0.0209 -1.9015 + 9.000 1.0659 0.0237 -2.0501 + 10.000 1.1068 0.0270 -2.2053 + 11.000 1.1146 0.0328 -2.3201 + 12.000 1.1437 0.0380 -2.5649 + 13.000 1.1530 0.0457 -2.7732 + 14.000 1.1785 0.0527 -3.0315 + 15.000 1.1965 0.0611 -3.2835 + 16.000 1.2243 0.0693 -3.5810 + 17.000 1.2486 0.0782 -3.8873 + 18.000 1.2711 0.0879 -4.2109 + 19.000 1.2921 0.0982 -4.5349 + 20.000 1.3103 0.1092 -4.8694 + 21.000 1.3273 0.1205 -5.2118 + 22.000 1.3464 0.1314 -5.5795 + 23.000 1.3547 0.1441 -5.9129 + 24.000 1.3612 0.1569 -6.2417 + 25.000 1.3621 0.1702 -6.5518 + 26.000 1.3574 0.1844 -6.8172 + 28.000 1.3331 0.2134 -7.2030 + 29.000 1.3151 0.2296 -7.3009 + 30.000 1.3037 0.2442 -7.4214 + 40.000 1.0724 0.4510 -1.0500 + 50.000 0.8792 0.6723 -1.0500 + 60.000 0.6770 0.8824 -1.0500 + 70.000 0.4561 1.0569 -1.0500 + 80.000 0.2243 1.1758 -1.0500 + 90.000 0.0000 1.2263 -1.0500 + 100.000 -0.1570 1.1758 -1.0500 + 110.000 -0.3193 1.0569 -1.0500 + 120.000 -0.4739 0.8824 -1.0500 + 130.000 -0.6154 0.6723 -1.0500 + 140.000 -0.7507 0.4510 -1.0500 + 150.000 -0.9126 0.2442 -1.0500 + 160.000 -0.6084 0.0763 -1.0500 + 170.000 -0.3042 0.0173 -1.0500 + 180.000 0.0000 0.0173 -1.0500 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0265 -1.0500 + -170.000 0.3188 0.0265 -1.0500 + -160.000 0.6377 0.0740 -1.0500 + -150.000 0.9566 0.2428 -1.0500 + -140.000 0.7775 0.4507 -1.0500 + -130.000 0.6312 0.6735 -1.0500 + -120.000 0.4824 0.8854 -1.0500 + -110.000 0.3229 1.0619 -1.0500 + -100.000 0.1579 1.1829 -1.0500 + -90.000 0.0000 1.2355 -1.0500 + -80.000 -0.1579 1.1829 -1.0500 + -70.000 -0.3229 1.0619 -1.0500 + -60.000 -0.4824 0.8854 -1.0500 + -50.000 -0.6312 0.6735 -1.0500 + -40.000 -0.7775 0.4507 -1.0500 + -30.000 -0.9566 0.2428 -1.0500 + -20.000 -0.6990 0.1374 -1.0500 + -10.000 -0.6305 0.0320 -2.4763 + -9.000 -0.5846 0.0296 -2.2114 + -8.000 -0.5656 0.0276 -2.0071 + -7.000 -0.4826 0.0265 -1.7052 + -6.000 -0.3812 0.0257 -1.4476 + -5.000 -0.2740 0.0250 -1.2528 + -4.000 -0.1598 0.0246 -1.0679 + -3.000 -0.0443 0.0239 -0.9516 + -1.000 0.1932 0.0231 -1.0446 + 0.000 0.3133 0.0230 -1.1332 + 1.000 0.4312 0.0232 -1.2224 + 2.000 0.5504 0.0232 -1.3133 + 5.000 0.8753 0.0248 -1.5949 + 6.000 0.9525 0.0262 -1.6950 + 7.000 1.0053 0.0274 -1.7871 + 9.000 1.1044 0.0311 -2.0976 + 10.000 1.1238 0.0351 -2.2272 + 11.000 1.1576 0.0392 -2.4030 + 12.000 1.1727 0.0451 -2.6260 + 13.000 1.2005 0.0510 -2.8799 + 14.000 1.2286 0.0574 -3.1581 + 15.000 1.2617 0.0640 -3.4600 + 16.000 1.2886 0.0717 -3.7722 + 17.000 1.3161 0.0798 -4.1116 + 18.000 1.3390 0.0889 -4.4496 + 19.000 1.3617 0.0985 -4.7969 + 20.000 1.3762 0.1095 -5.1410 + 21.000 1.3913 0.1207 -5.4920 + 22.000 1.4044 0.1325 -5.8568 + 23.000 1.4088 0.1454 -6.1886 + 24.000 1.4222 0.1569 -6.5916 + 25.000 1.4229 0.1701 -6.9257 + 26.000 1.4236 0.1831 -7.2526 + 27.000 1.4198 0.1966 -7.5420 + 28.000 1.4120 0.2107 -7.7888 + 29.000 1.3826 0.2276 -7.8548 + 30.000 1.3666 0.2428 -7.9826 + 40.000 1.1106 0.4507 -1.0500 + 50.000 0.9018 0.6735 -1.0500 + 60.000 0.6891 0.8854 -1.0500 + 70.000 0.4613 1.0619 -1.0500 + 80.000 0.2255 1.1829 -1.0500 + 90.000 0.0000 1.2355 -1.0500 + 100.000 -0.1579 1.1829 -1.0500 + 110.000 -0.3229 1.0619 -1.0500 + 120.000 -0.4824 0.8854 -1.0500 + 130.000 -0.6312 0.6735 -1.0500 + 140.000 -0.7775 0.4507 -1.0500 + 150.000 -0.9566 0.2428 -1.0500 + 160.000 -0.6377 0.0740 -1.0500 + 170.000 -0.3188 0.0265 -1.0500 + 180.000 0.0000 0.0265 -1.0500 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0273 -1.0500 + -170.000 0.3307 0.0273 -1.0500 + -160.000 0.6614 0.0659 -1.0500 + -150.000 0.9922 0.2354 -1.0500 + -140.000 0.7991 0.4443 -1.0500 + -130.000 0.6440 0.6682 -1.0500 + -120.000 0.4893 0.8814 -1.0500 + -110.000 0.3258 1.0594 -1.0500 + -100.000 0.1586 1.1821 -1.0500 + -90.000 0.0000 1.2363 -1.0500 + -80.000 -0.1586 1.1821 -1.0500 + -70.000 -0.3258 1.0594 -1.0500 + -60.000 -0.4893 0.8814 -1.0500 + -50.000 -0.6440 0.6682 -1.0500 + -40.000 -0.7991 0.4443 -1.0500 + -30.000 -0.9922 0.2354 -1.0500 + -20.000 -0.7259 0.1333 -1.0500 + -10.000 -0.6565 0.0312 -2.5308 + -9.000 -0.6153 0.0291 -2.2680 + -8.000 -0.5760 0.0277 -2.0253 + -7.000 -0.4843 0.0269 -1.7079 + -6.000 -0.3829 0.0261 -1.4501 + -5.000 -0.2719 0.0254 -1.2506 + -4.000 -0.1571 0.0250 -1.0648 + -3.000 -0.0409 0.0245 -0.9496 + -2.000 0.0773 0.0237 -0.9639 + -1.000 0.1974 0.0234 -1.0472 + 0.000 0.3173 0.0234 -1.1354 + 1.000 0.4378 0.0234 -1.2266 + 2.000 0.5540 0.0237 -1.3159 + 4.000 0.7767 0.0246 -1.5044 + 5.000 0.8722 0.0257 -1.5946 + 6.000 0.9556 0.0269 -1.6904 + 7.000 1.0185 0.0277 -1.8002 + 8.000 1.0788 0.0289 -1.9584 + 9.000 1.1126 0.0313 -2.1073 + 10.000 1.1482 0.0346 -2.2605 + 11.000 1.1714 0.0390 -2.4300 + 12.000 1.2007 0.0438 -2.6851 + 13.000 1.2270 0.0496 -2.9404 + 14.000 1.2643 0.0552 -3.2479 + 15.000 1.2937 0.0619 -3.5495 + 16.000 1.3227 0.0691 -3.8735 + 17.000 1.3492 0.0771 -4.2206 + 19.000 1.3921 0.0955 -4.9136 + 20.000 1.4242 0.1039 -5.3363 + 21.000 1.4362 0.1152 -5.6847 + 22.000 1.4437 0.1275 -6.0421 + 23.000 1.4482 0.1403 -6.3916 + 24.000 1.4544 0.1528 -6.7718 + 25.000 1.4570 0.1657 -7.1295 + 26.000 1.4545 0.1791 -7.4507 + 27.000 1.4477 0.1930 -7.7327 + 28.000 1.4396 0.2069 -7.9910 + 29.000 1.4298 0.2210 -8.2200 + 30.000 1.4174 0.2354 -8.4060 + 40.000 1.1415 0.4443 -1.0500 + 50.000 0.9200 0.6682 -1.0500 + 60.000 0.6990 0.8814 -1.0500 + 70.000 0.4656 1.0594 -1.0500 + 80.000 0.2266 1.1821 -1.0500 + 90.000 0.0000 1.2363 -1.0500 + 100.000 -0.1586 1.1821 -1.0500 + 110.000 -0.3258 1.0594 -1.0500 + 120.000 -0.4893 0.8814 -1.0500 + 130.000 -0.6440 0.6682 -1.0500 + 140.000 -0.7991 0.4443 -1.0500 + 150.000 -0.9922 0.2354 -1.0500 + 160.000 -0.6614 0.0659 -1.0500 + 170.000 -0.3307 0.0273 -1.0500 + 180.000 0.0000 0.0273 -1.0500 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0273 -1.0500 + -170.000 0.3963 0.0273 -1.0500 + -160.000 0.7927 0.0815 -1.0500 + -150.000 0.9345 0.2497 -1.0500 + -140.000 0.7640 0.4570 -1.0500 + -130.000 0.6233 0.6789 -1.0500 + -120.000 0.4781 0.8897 -1.0500 + -110.000 0.3211 1.0650 -1.0500 + -100.000 0.1575 1.1850 -1.0500 + -90.000 0.0000 1.2363 -1.0500 + -80.000 -0.1575 1.1850 -1.0500 + -70.000 -0.3211 1.0650 -1.0500 + -60.000 -0.4781 0.8897 -1.0500 + -50.000 -0.6233 0.6789 -1.0500 + -40.000 -0.7640 0.4570 -1.0500 + -30.000 -0.9345 0.2497 -1.0500 + -20.000 -0.8190 0.1218 -1.0500 + -10.000 -0.6664 0.0308 -2.5594 + -9.000 -0.6387 0.0282 -2.3121 + -8.000 -0.5840 0.0273 -2.0395 + -5.000 -0.2715 0.0252 -1.2500 + -4.000 -0.1565 0.0247 -1.0642 + -3.000 -0.0386 0.0243 -0.9387 + -2.000 0.0795 0.0237 -0.9652 + -1.000 0.1995 0.0234 -1.0481 + 0.000 0.3206 0.0233 -1.1376 + 1.000 0.4392 0.0233 -1.2274 + 2.000 0.5554 0.0235 -1.3173 + 3.000 0.6697 0.0239 -1.4100 + 4.000 0.7759 0.0247 -1.4949 + 6.000 0.9617 0.0267 -1.6893 + 7.000 1.0370 0.0273 -1.8165 + 8.000 1.0937 0.0284 -1.9758 + 9.000 1.1244 0.0309 -2.1223 + 11.000 1.1836 0.0383 -2.4539 + 12.000 1.2209 0.0425 -2.7277 + 13.000 1.2599 0.0471 -3.0189 + 15.000 1.3283 0.0587 -3.6464 + 16.000 1.3574 0.0657 -3.9802 + 17.000 1.3869 0.0731 -4.3450 + 18.000 1.4070 0.0819 -4.6864 + 19.000 1.4296 0.0909 -5.0580 + 20.000 1.4449 0.1014 -5.4198 + 22.000 1.4619 0.1250 -6.1264 + 25.000 1.4735 0.1633 -7.2267 + 26.000 1.4721 0.1765 -7.5605 + 30.000 1.3351 0.2497 -6.1002 + 40.000 1.0915 0.4570 -1.0500 + 50.000 0.8905 0.6789 -1.0500 + 60.000 0.6831 0.8897 -1.0500 + 70.000 0.4587 1.0650 -1.0500 + 80.000 0.2249 1.1850 -1.0500 + 90.000 0.0000 1.2363 -1.0500 + 100.000 -0.1575 1.1850 -1.0500 + 110.000 -0.3211 1.0650 -1.0500 + 120.000 -0.4781 0.8897 -1.0500 + 130.000 -0.6233 0.6789 -1.0500 + 140.000 -0.7640 0.4570 -1.0500 + 150.000 -0.9345 0.2497 -1.0500 + 160.000 -0.7927 0.0815 -1.0500 + 170.000 -0.3963 0.0273 -1.0500 + 180.000 0.0000 0.0273 -1.0500 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0273 -1.0500 + -170.000 0.3420 0.0273 -1.0500 + -160.000 0.6842 0.0565 -1.0500 + -150.000 1.0262 0.2268 -1.0500 + -140.000 0.8198 0.4367 -1.0500 + -130.000 0.6563 0.6619 -1.0500 + -120.000 0.4958 0.8765 -1.0500 + -110.000 0.3287 1.0560 -1.0500 + -100.000 0.1593 1.1804 -1.0500 + -90.000 0.0000 1.2363 -1.0500 + -80.000 -0.1593 1.1804 -1.0500 + -70.000 -0.3287 1.0560 -1.0500 + -60.000 -0.4958 0.8765 -1.0500 + -50.000 -0.6563 0.6619 -1.0500 + -40.000 -0.8198 0.4367 -1.0500 + -30.000 -1.0262 0.2268 -1.0500 + -20.000 -0.7455 0.1287 -1.0500 + -10.000 -0.6641 0.0307 -2.5362 + -9.000 -0.6680 0.0278 -2.3705 + -8.000 -0.5909 0.0270 -2.0519 + -6.000 -0.3842 0.0255 -1.4542 + -4.000 -0.1556 0.0245 -1.0634 + -3.000 -0.0378 0.0242 -0.9399 + -2.000 0.0809 0.0237 -0.9660 + -1.000 0.2015 0.0233 -1.0494 + 0.000 0.3219 0.0232 -1.1383 + 1.000 0.4399 0.0233 -1.2279 + 2.000 0.5557 0.0235 -1.3193 + 4.000 0.7740 0.0248 -1.4904 + 5.000 0.8707 0.0258 -1.5838 + 6.000 0.9649 0.0266 -1.6955 + 7.000 1.0572 0.0272 -1.8344 + 8.000 1.1003 0.0283 -1.9832 + 9.000 1.1403 0.0303 -2.1425 + 10.000 1.1576 0.0340 -2.2577 + 11.000 1.2042 0.0371 -2.4950 + 12.000 1.2389 0.0413 -2.7658 + 13.000 1.2767 0.0460 -3.0586 + 14.000 1.3142 0.0511 -3.3735 + 16.000 1.3779 0.0638 -4.0437 + 17.000 1.4021 0.0715 -4.3944 + 18.000 1.4265 0.0798 -4.7538 + 19.000 1.4454 0.0891 -5.1180 + 20.000 1.4597 0.0995 -5.4792 + 21.000 1.4671 0.1111 -5.8193 + 24.000 1.5049 0.1452 -7.0494 + 25.000 1.5085 0.1578 -7.4313 + 26.000 1.5089 0.1708 -7.7900 + 27.000 1.5050 0.1839 -8.1148 + 28.000 1.4955 0.1978 -8.3910 + 29.000 1.4817 0.2122 -8.6188 + 30.000 1.4660 0.2268 -8.8098 + 40.000 1.1712 0.4367 -1.0500 + 50.000 0.9375 0.6619 -1.0500 + 60.000 0.7083 0.8765 -1.0500 + 70.000 0.4696 1.0560 -1.0500 + 80.000 0.2276 1.1804 -1.0500 + 90.000 0.0000 1.2363 -1.0500 + 100.000 -0.1593 1.1804 -1.0500 + 110.000 -0.3287 1.0560 -1.0500 + 120.000 -0.4958 0.8765 -1.0500 + 130.000 -0.6563 0.6619 -1.0500 + 140.000 -0.8198 0.4367 -1.0500 + 150.000 -1.0262 0.2268 -1.0500 + 160.000 -0.6842 0.0565 -1.0500 + 170.000 -0.3420 0.0273 -1.0500 + 180.000 0.0000 0.0273 -1.0500 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0273 -1.0500 + -170.000 0.3603 0.0273 -1.0500 + -160.000 0.7204 0.0597 -1.0500 + -150.000 1.0186 0.2297 -1.0500 + -140.000 0.8152 0.4393 -1.0500 + -130.000 0.6535 0.6640 -1.0500 + -120.000 0.4943 0.8781 -1.0500 + -110.000 0.3281 1.0571 -1.0500 + -100.000 0.1591 1.1810 -1.0500 + -90.000 0.0000 1.2363 -1.0500 + -80.000 -0.1591 1.1810 -1.0500 + -70.000 -0.3281 1.0571 -1.0500 + -60.000 -0.4943 0.8781 -1.0500 + -50.000 -0.6535 0.6640 -1.0500 + -40.000 -0.8152 0.4393 -1.0500 + -30.000 -1.0186 0.2297 -1.0500 + -20.000 -0.7743 0.1250 -1.0500 + -10.000 -0.6770 0.0301 -2.5650 + -7.000 -0.4925 0.0261 -1.7218 + -6.000 -0.3833 0.0255 -1.4432 + -5.000 -0.2711 0.0248 -1.2500 + -4.000 -0.1555 0.0244 -1.0630 + -3.000 -0.0370 0.0241 -0.9427 + -2.000 0.0825 0.0237 -0.9667 + -1.000 0.2026 0.0232 -1.0502 + 0.000 0.3227 0.0232 -1.1385 + 1.000 0.4406 0.0232 -1.2287 + 2.000 0.5565 0.0234 -1.3154 + 3.000 0.6691 0.0239 -1.4003 + 4.000 0.7744 0.0247 -1.4940 + 5.000 0.8714 0.0257 -1.5865 + 6.000 0.9716 0.0263 -1.7018 + 7.000 1.0646 0.0270 -1.8417 + 8.000 1.1070 0.0281 -1.9911 + 10.000 1.1726 0.0332 -2.2830 + 11.000 1.2166 0.0364 -2.5199 + 12.000 1.2588 0.0401 -2.8083 + 13.000 1.2986 0.0444 -3.1107 + 14.000 1.3278 0.0502 -3.4075 + 15.000 1.3609 0.0560 -3.7370 + 17.000 1.4166 0.0702 -4.4417 + 18.000 1.4395 0.0784 -4.7983 + 19.000 1.4582 0.0877 -5.1665 + 20.000 1.4677 0.0985 -5.5106 + 22.000 1.5073 0.1186 -6.3371 + 23.000 1.5150 0.1307 -6.7366 + 24.000 1.5205 0.1430 -7.1348 + 25.000 1.5231 0.1558 -7.5156 + 26.000 1.5222 0.1688 -7.8715 + 27.000 1.5151 0.1824 -8.1811 + 28.000 1.5047 0.1964 -8.4551 + 29.000 1.4923 0.2106 -8.6982 + 30.000 1.4552 0.2297 -8.2297 + 40.000 1.1645 0.4393 -1.0500 + 50.000 0.9336 0.6640 -1.0500 + 60.000 0.7062 0.8781 -1.0500 + 70.000 0.4687 1.0571 -1.0500 + 80.000 0.2274 1.1810 -1.0500 + 90.000 0.0000 1.2363 -1.0500 + 100.000 -0.1591 1.1810 -1.0500 + 110.000 -0.3281 1.0571 -1.0500 + 120.000 -0.4943 0.8781 -1.0500 + 130.000 -0.6535 0.6640 -1.0500 + 140.000 -0.8152 0.4393 -1.0500 + 150.000 -1.0186 0.2297 -1.0500 + 160.000 -0.7204 0.0597 -1.0500 + 170.000 -0.3603 0.0273 -1.0500 + 180.000 0.0000 0.0273 -1.0500 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0273 -1.0500 + -170.000 0.3472 0.0273 -1.0500 + -160.000 0.6943 0.0527 -1.0500 + -150.000 1.0415 0.2232 -1.0500 + -140.000 0.8291 0.4335 -1.0500 + -130.000 0.6617 0.6592 -1.0500 + -120.000 0.4987 0.8744 -1.0500 + -110.000 0.3299 1.0546 -1.0500 + -100.000 0.1596 1.1796 -1.0500 + -90.000 0.0000 1.2363 -1.0500 + -80.000 -0.1596 1.1796 -1.0500 + -70.000 -0.3299 1.0546 -1.0500 + -60.000 -0.4987 0.8744 -1.0500 + -50.000 -0.6617 0.6592 -1.0500 + -40.000 -0.8291 0.4335 -1.0500 + -30.000 -1.0415 0.2232 -1.0500 + -20.000 -0.7623 0.1264 -1.0500 + -10.000 -0.6901 0.0296 -2.5924 + -9.000 -0.6710 0.0277 -2.3634 + -8.000 -0.5974 0.0265 -2.0643 + -6.000 -0.3832 0.0254 -1.4409 + -5.000 -0.2711 0.0247 -1.2497 + -4.000 -0.1554 0.0242 -1.0629 + -3.000 -0.0362 0.0240 -0.9430 + -2.000 0.0836 0.0236 -0.9674 + -1.000 0.2031 0.0232 -1.0504 + 0.000 0.3237 0.0231 -1.1393 + 1.000 0.4395 0.0233 -1.2289 + 2.000 0.5564 0.0234 -1.3146 + 3.000 0.6678 0.0240 -1.3986 + 5.000 0.8744 0.0256 -1.5898 + 6.000 0.9745 0.0263 -1.7051 + 7.000 1.0719 0.0268 -1.8489 + 8.000 1.1111 0.0279 -1.9955 + 11.000 1.2280 0.0358 -2.5425 + 12.000 1.2701 0.0394 -2.8321 + 14.000 1.3483 0.0485 -3.4590 + 16.000 1.4021 0.0617 -4.1188 + 18.000 1.4504 0.0773 -4.8357 + 21.000 1.5090 0.1056 -6.0025 + 22.000 1.5189 0.1170 -6.3899 + 23.000 1.5276 0.1289 -6.8015 + 24.000 1.5322 0.1413 -7.1982 + 25.000 1.5338 0.1542 -7.5766 + 26.000 1.5294 0.1677 -7.9162 + 27.000 1.5225 0.1813 -8.2290 + 28.000 1.5133 0.1950 -8.5152 + 29.000 1.5021 0.2090 -8.7703 + 30.000 1.4878 0.2232 -8.9852 + 40.000 1.1844 0.4335 -1.0500 + 50.000 0.9454 0.6592 -1.0500 + 60.000 0.7125 0.8744 -1.0500 + 70.000 0.4714 1.0546 -1.0500 + 80.000 0.2281 1.1796 -1.0500 + 90.000 0.0000 1.2363 -1.0500 + 100.000 -0.1596 1.1796 -1.0500 + 110.000 -0.3299 1.0546 -1.0500 + 120.000 -0.4987 0.8744 -1.0500 + 130.000 -0.6617 0.6592 -1.0500 + 140.000 -0.8291 0.4335 -1.0500 + 150.000 -1.0415 0.2232 -1.0500 + 160.000 -0.6943 0.0527 -1.0500 + 170.000 -0.3472 0.0273 -1.0500 + 180.000 0.0000 0.0273 -1.0500 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0259_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0259_coords.txt new file mode 100644 index 00000000..94bdcf9e --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0259_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0259 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.022584 + 0.027091 0.047510 + 0.060263 0.073301 + 0.105430 0.097140 + 0.161359 0.117917 + 0.226526 0.134137 + 0.299152 0.144379 + 0.377257 0.146668 + 0.458710 0.140419 + 0.541290 0.127194 + 0.622743 0.109034 + 0.700848 0.088223 + 0.773474 0.067204 + 0.838641 0.048007 + 0.894570 0.031887 + 0.939737 0.019298 + 0.972909 0.010124 + 0.993181 0.003839 + 1.000000 0.000000 + 0.993181 -0.001378 + 0.972909 -0.002676 + 0.939737 -0.005710 + 0.894570 -0.011838 + 0.838641 -0.021843 + 0.773474 -0.035786 + 0.700848 -0.052933 + 0.622743 -0.071538 + 0.541290 -0.089257 + 0.458710 -0.103644 + 0.377257 -0.112299 + 0.299152 -0.113402 + 0.226526 -0.107598 + 0.161359 -0.096465 + 0.105430 -0.081252 + 0.060263 -0.062864 + 0.027091 -0.042119 + 0.006819 -0.020381 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0276.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0276.dat new file mode 100644 index 00000000..05644926 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0276.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0276 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0276_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0237 -1.0947 + -170.000 0.2972 0.0237 -1.0947 + -160.000 0.5944 0.0815 -1.0947 + -150.000 0.8917 0.2455 -1.0947 + -140.000 0.7334 0.4476 -1.0947 + -130.000 0.6013 0.6637 -1.0947 + -120.000 0.4631 0.8690 -1.0947 + -110.000 0.3120 1.0395 -1.0947 + -100.000 0.1534 1.1557 -1.0947 + -90.000 0.0000 1.2050 -1.0947 + -80.000 -0.1534 1.1557 -1.0947 + -70.000 -0.3120 1.0395 -1.0947 + -60.000 -0.4631 0.8690 -1.0947 + -50.000 -0.6013 0.6637 -1.0947 + -40.000 -0.7334 0.4476 -1.0947 + -30.000 -0.8917 0.2455 -1.0947 + -20.000 -0.6461 0.1386 -1.0947 + -10.000 -0.5722 0.0316 -2.3958 + -9.000 -0.5433 0.0285 -2.1764 + -8.000 -0.5145 0.0260 -1.9643 + -7.000 -0.4633 0.0248 -1.7200 + -6.000 -0.3726 0.0238 -1.4829 + -5.000 -0.2695 0.0231 -1.2946 + -4.000 -0.1619 0.0224 -1.1182 + -3.000 -0.0521 0.0215 -1.0047 + -2.000 0.0639 0.0213 -1.0040 + -1.000 0.1795 0.0212 -1.0841 + 0.000 0.2946 0.0213 -1.1688 + 1.000 0.4103 0.0213 -1.2561 + 2.000 0.5242 0.0215 -1.3432 + 3.000 0.6361 0.0216 -1.4336 + 4.000 0.7437 0.0220 -1.5246 + 5.000 0.8498 0.0224 -1.6245 + 6.000 0.9364 0.0235 -1.7280 + 7.000 0.9713 0.0251 -1.8062 + 8.000 1.0028 0.0273 -1.9267 + 9.000 1.0414 0.0300 -2.0719 + 10.000 1.0814 0.0333 -2.2235 + 11.000 1.0890 0.0389 -2.3357 + 12.000 1.1174 0.0440 -2.5748 + 13.000 1.1266 0.0516 -2.7784 + 14.000 1.1514 0.0584 -3.0308 + 15.000 1.1691 0.0666 -3.2770 + 16.000 1.1962 0.0746 -3.5677 + 17.000 1.2199 0.0833 -3.8669 + 18.000 1.2419 0.0928 -4.1831 + 19.000 1.2624 0.1028 -4.4997 + 20.000 1.2802 0.1136 -4.8265 + 21.000 1.2968 0.1246 -5.1610 + 22.000 1.3155 0.1353 -5.5203 + 23.000 1.3236 0.1477 -5.8461 + 24.000 1.3300 0.1602 -6.1673 + 25.000 1.3308 0.1732 -6.4703 + 26.000 1.3263 0.1870 -6.7296 + 28.000 1.3025 0.2154 -7.1066 + 29.000 1.2849 0.2312 -7.2022 + 30.000 1.2738 0.2455 -7.3200 + 40.000 1.0478 0.4476 -1.0947 + 50.000 0.8590 0.6637 -1.0947 + 60.000 0.6615 0.8690 -1.0947 + 70.000 0.4456 1.0395 -1.0947 + 80.000 0.2191 1.1557 -1.0947 + 90.000 0.0000 1.2050 -1.0947 + 100.000 -0.1534 1.1557 -1.0947 + 110.000 -0.3120 1.0395 -1.0947 + 120.000 -0.4631 0.8690 -1.0947 + 130.000 -0.6013 0.6637 -1.0947 + 140.000 -0.7334 0.4476 -1.0947 + 150.000 -0.8917 0.2455 -1.0947 + 160.000 -0.5944 0.0815 -1.0947 + 170.000 -0.2972 0.0237 -1.0947 + 180.000 0.0000 0.0237 -1.0947 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0413 -1.0947 + -170.000 0.3115 0.0413 -1.0947 + -160.000 0.6231 0.0877 -1.0947 + -150.000 0.9346 0.2526 -1.0947 + -140.000 0.7596 0.4558 -1.0947 + -130.000 0.6167 0.6734 -1.0947 + -120.000 0.4714 0.8804 -1.0947 + -110.000 0.3155 1.0529 -1.0947 + -100.000 0.1542 1.1712 -1.0947 + -90.000 0.0000 1.2225 -1.0947 + -80.000 -0.1542 1.1712 -1.0947 + -70.000 -0.3155 1.0529 -1.0947 + -60.000 -0.4714 0.8804 -1.0947 + -50.000 -0.6167 0.6734 -1.0947 + -40.000 -0.7596 0.4558 -1.0947 + -30.000 -0.9346 0.2526 -1.0947 + -20.000 -0.6829 0.1496 -1.0947 + -10.000 -0.6161 0.0466 -2.4883 + -9.000 -0.5712 0.0443 -2.2295 + -8.000 -0.5526 0.0423 -2.0298 + -7.000 -0.4716 0.0413 -1.7349 + -6.000 -0.3725 0.0405 -1.4832 + -5.000 -0.2677 0.0398 -1.2929 + -4.000 -0.1561 0.0394 -1.1123 + -3.000 -0.0432 0.0387 -0.9986 + -1.000 0.1888 0.0379 -1.0895 + 0.000 0.3061 0.0378 -1.1760 + 1.000 0.4213 0.0380 -1.2632 + 2.000 0.5378 0.0380 -1.3520 + 5.000 0.8552 0.0396 -1.6272 + 6.000 0.9306 0.0410 -1.7249 + 7.000 0.9823 0.0421 -1.8149 + 9.000 1.0790 0.0457 -2.1183 + 10.000 1.0980 0.0496 -2.2449 + 11.000 1.1311 0.0536 -2.4167 + 12.000 1.1458 0.0595 -2.6346 + 13.000 1.1730 0.0652 -2.8826 + 14.000 1.2004 0.0715 -3.1545 + 15.000 1.2328 0.0779 -3.4495 + 16.000 1.2590 0.0855 -3.7545 + 17.000 1.2859 0.0934 -4.0861 + 18.000 1.3082 0.1022 -4.4164 + 19.000 1.3304 0.1116 -4.7557 + 20.000 1.3446 0.1223 -5.0919 + 21.000 1.3594 0.1333 -5.4348 + 22.000 1.3722 0.1448 -5.7913 + 23.000 1.3765 0.1574 -6.1155 + 24.000 1.3896 0.1686 -6.5092 + 25.000 1.3903 0.1816 -6.8357 + 26.000 1.3909 0.1943 -7.1550 + 27.000 1.3872 0.2075 -7.4378 + 28.000 1.3796 0.2212 -7.6789 + 29.000 1.3509 0.2378 -7.7434 + 30.000 1.3352 0.2526 -7.8683 + 40.000 1.0851 0.4558 -1.0947 + 50.000 0.8811 0.6734 -1.0947 + 60.000 0.6733 0.8804 -1.0947 + 70.000 0.4507 1.0529 -1.0947 + 80.000 0.2203 1.1712 -1.0947 + 90.000 0.0000 1.2225 -1.0947 + 100.000 -0.1542 1.1712 -1.0947 + 110.000 -0.3155 1.0529 -1.0947 + 120.000 -0.4714 0.8804 -1.0947 + 130.000 -0.6167 0.6734 -1.0947 + 140.000 -0.7596 0.4558 -1.0947 + 150.000 -0.9346 0.2526 -1.0947 + 160.000 -0.6231 0.0877 -1.0947 + 170.000 -0.3115 0.0413 -1.0947 + 180.000 0.0000 0.0413 -1.0947 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0427 -1.0947 + -170.000 0.3231 0.0427 -1.0947 + -160.000 0.6463 0.0804 -1.0947 + -150.000 0.9694 0.2461 -1.0947 + -140.000 0.7808 0.4501 -1.0947 + -130.000 0.6292 0.6689 -1.0947 + -120.000 0.4780 0.8773 -1.0947 + -110.000 0.3184 1.0511 -1.0947 + -100.000 0.1550 1.1711 -1.0947 + -90.000 0.0000 1.2239 -1.0947 + -80.000 -0.1550 1.1711 -1.0947 + -70.000 -0.3184 1.0511 -1.0947 + -60.000 -0.4780 0.8773 -1.0947 + -50.000 -0.6292 0.6689 -1.0947 + -40.000 -0.7808 0.4501 -1.0947 + -30.000 -0.9694 0.2461 -1.0947 + -20.000 -0.7092 0.1463 -1.0947 + -10.000 -0.6414 0.0466 -2.5416 + -9.000 -0.6012 0.0445 -2.2848 + -8.000 -0.5628 0.0432 -2.0477 + -7.000 -0.4732 0.0423 -1.7376 + -6.000 -0.3741 0.0415 -1.4857 + -5.000 -0.2657 0.0409 -1.2907 + -4.000 -0.1535 0.0405 -1.1092 + -3.000 -0.0399 0.0400 -0.9966 + -2.000 0.0755 0.0393 -1.0106 + -1.000 0.1929 0.0390 -1.0920 + 0.000 0.3100 0.0390 -1.1782 + 1.000 0.4277 0.0390 -1.2673 + 2.000 0.5413 0.0393 -1.3545 + 4.000 0.7589 0.0401 -1.5387 + 5.000 0.8522 0.0412 -1.6269 + 6.000 0.9337 0.0423 -1.7204 + 7.000 0.9951 0.0432 -1.8277 + 8.000 1.0541 0.0443 -1.9823 + 9.000 1.0870 0.0467 -2.1278 + 10.000 1.1218 0.0498 -2.2774 + 11.000 1.1445 0.0541 -2.4431 + 12.000 1.1732 0.0589 -2.6923 + 13.000 1.1989 0.0645 -2.9418 + 14.000 1.2353 0.0700 -3.2423 + 15.000 1.2640 0.0765 -3.5369 + 16.000 1.2923 0.0836 -3.8535 + 17.000 1.3183 0.0914 -4.1926 + 19.000 1.3602 0.1094 -4.8697 + 20.000 1.3915 0.1176 -5.2827 + 21.000 1.4032 0.1286 -5.6231 + 22.000 1.4106 0.1406 -5.9723 + 23.000 1.4149 0.1531 -6.3138 + 24.000 1.4210 0.1654 -6.6853 + 25.000 1.4236 0.1780 -7.0348 + 26.000 1.4211 0.1910 -7.3486 + 27.000 1.4145 0.2046 -7.6241 + 28.000 1.4066 0.2183 -7.8765 + 29.000 1.3970 0.2320 -8.1002 + 30.000 1.3848 0.2461 -8.2820 + 40.000 1.1153 0.4501 -1.0947 + 50.000 0.8989 0.6689 -1.0947 + 60.000 0.6829 0.8773 -1.0947 + 70.000 0.4549 1.0511 -1.0947 + 80.000 0.2214 1.1711 -1.0947 + 90.000 0.0000 1.2239 -1.0947 + 100.000 -0.1550 1.1711 -1.0947 + 110.000 -0.3184 1.0511 -1.0947 + 120.000 -0.4780 0.8773 -1.0947 + 130.000 -0.6292 0.6689 -1.0947 + 140.000 -0.7808 0.4501 -1.0947 + 150.000 -0.9694 0.2461 -1.0947 + 160.000 -0.6463 0.0804 -1.0947 + 170.000 -0.3231 0.0427 -1.0947 + 180.000 0.0000 0.0427 -1.0947 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0427 -1.0947 + -170.000 0.3872 0.0427 -1.0947 + -160.000 0.7745 0.0957 -1.0947 + -150.000 0.9131 0.2601 -1.0947 + -140.000 0.7465 0.4626 -1.0947 + -130.000 0.6090 0.6794 -1.0947 + -120.000 0.4672 0.8854 -1.0947 + -110.000 0.3137 1.0567 -1.0947 + -100.000 0.1539 1.1738 -1.0947 + -90.000 0.0000 1.2239 -1.0947 + -80.000 -0.1539 1.1738 -1.0947 + -70.000 -0.3137 1.0567 -1.0947 + -60.000 -0.4672 0.8854 -1.0947 + -50.000 -0.6090 0.6794 -1.0947 + -40.000 -0.7465 0.4626 -1.0947 + -30.000 -0.9131 0.2601 -1.0947 + -20.000 -0.8002 0.1351 -1.0947 + -10.000 -0.6511 0.0461 -2.5695 + -9.000 -0.6241 0.0436 -2.3279 + -8.000 -0.5706 0.0427 -2.0616 + -5.000 -0.2653 0.0407 -1.2901 + -4.000 -0.1529 0.0402 -1.1086 + -3.000 -0.0377 0.0398 -0.9859 + -2.000 0.0776 0.0393 -1.0119 + -1.000 0.1949 0.0389 -1.0929 + 0.000 0.3132 0.0388 -1.1803 + 1.000 0.4292 0.0388 -1.2680 + 2.000 0.5426 0.0391 -1.3559 + 3.000 0.6544 0.0394 -1.4464 + 4.000 0.7581 0.0402 -1.5294 + 6.000 0.9397 0.0421 -1.7194 + 7.000 1.0132 0.0428 -1.8437 + 8.000 1.0686 0.0438 -1.9993 + 9.000 1.0986 0.0462 -2.1424 + 11.000 1.1565 0.0534 -2.4664 + 12.000 1.1929 0.0575 -2.7339 + 13.000 1.2310 0.0621 -3.0185 + 15.000 1.2979 0.0735 -3.6316 + 16.000 1.3263 0.0802 -3.9577 + 17.000 1.3551 0.0875 -4.3142 + 18.000 1.3747 0.0960 -4.6477 + 19.000 1.3968 0.1049 -5.0108 + 20.000 1.4117 0.1151 -5.3642 + 22.000 1.4284 0.1382 -6.0547 + 25.000 1.4397 0.1756 -7.1298 + 26.000 1.4383 0.1885 -7.4558 + 30.000 1.3044 0.2601 -6.0291 + 40.000 1.0665 0.4626 -1.0947 + 50.000 0.8700 0.6794 -1.0947 + 60.000 0.6674 0.8854 -1.0947 + 70.000 0.4482 1.0567 -1.0947 + 80.000 0.2198 1.1738 -1.0947 + 90.000 0.0000 1.2239 -1.0947 + 100.000 -0.1539 1.1738 -1.0947 + 110.000 -0.3137 1.0567 -1.0947 + 120.000 -0.4672 0.8854 -1.0947 + 130.000 -0.6090 0.6794 -1.0947 + 140.000 -0.7465 0.4626 -1.0947 + 150.000 -0.9131 0.2601 -1.0947 + 160.000 -0.7745 0.0957 -1.0947 + 170.000 -0.3872 0.0427 -1.0947 + 180.000 0.0000 0.0427 -1.0947 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0427 -1.0947 + -170.000 0.3342 0.0427 -1.0947 + -160.000 0.6685 0.0713 -1.0947 + -150.000 1.0026 0.2377 -1.0947 + -140.000 0.8010 0.4427 -1.0947 + -130.000 0.6412 0.6628 -1.0947 + -120.000 0.4844 0.8724 -1.0947 + -110.000 0.3211 1.0478 -1.0947 + -100.000 0.1557 1.1694 -1.0947 + -90.000 0.0000 1.2239 -1.0947 + -80.000 -0.1557 1.1694 -1.0947 + -70.000 -0.3211 1.0478 -1.0947 + -60.000 -0.4844 0.8724 -1.0947 + -50.000 -0.6412 0.6628 -1.0947 + -40.000 -0.8010 0.4427 -1.0947 + -30.000 -1.0026 0.2377 -1.0947 + -20.000 -0.7284 0.1419 -1.0947 + -10.000 -0.6488 0.0460 -2.5468 + -9.000 -0.6526 0.0433 -2.3850 + -8.000 -0.5774 0.0424 -2.0737 + -6.000 -0.3754 0.0410 -1.4897 + -4.000 -0.1520 0.0400 -1.1078 + -3.000 -0.0370 0.0397 -0.9872 + -2.000 0.0791 0.0393 -1.0126 + -1.000 0.1969 0.0388 -1.0942 + 0.000 0.3146 0.0387 -1.1810 + 1.000 0.4298 0.0388 -1.2686 + 2.000 0.5430 0.0391 -1.3579 + 4.000 0.7562 0.0403 -1.5250 + 5.000 0.8507 0.0413 -1.6163 + 6.000 0.9427 0.0420 -1.7254 + 7.000 1.0329 0.0426 -1.8611 + 8.000 1.0750 0.0437 -2.0065 + 9.000 1.1141 0.0456 -2.1622 + 10.000 1.1311 0.0493 -2.2748 + 11.000 1.1766 0.0523 -2.5065 + 12.000 1.2105 0.0564 -2.7712 + 13.000 1.2474 0.0610 -3.0573 + 14.000 1.2841 0.0660 -3.3650 + 16.000 1.3463 0.0784 -4.0198 + 17.000 1.3700 0.0859 -4.3625 + 18.000 1.3938 0.0940 -4.7136 + 19.000 1.4123 0.1031 -5.0694 + 20.000 1.4262 0.1133 -5.4224 + 21.000 1.4334 0.1246 -5.7546 + 24.000 1.4704 0.1580 -6.9565 + 25.000 1.4739 0.1702 -7.3296 + 26.000 1.4743 0.1829 -7.6801 + 27.000 1.4705 0.1958 -7.9975 + 28.000 1.4611 0.2093 -8.2673 + 29.000 1.4477 0.2234 -8.4899 + 30.000 1.4324 0.2377 -8.6765 + 40.000 1.1443 0.4427 -1.0947 + 50.000 0.9160 0.6628 -1.0947 + 60.000 0.6921 0.8724 -1.0947 + 70.000 0.4588 1.0478 -1.0947 + 80.000 0.2223 1.1694 -1.0947 + 90.000 0.0000 1.2239 -1.0947 + 100.000 -0.1557 1.1694 -1.0947 + 110.000 -0.3211 1.0478 -1.0947 + 120.000 -0.4844 0.8724 -1.0947 + 130.000 -0.6412 0.6628 -1.0947 + 140.000 -0.8010 0.4427 -1.0947 + 150.000 -1.0026 0.2377 -1.0947 + 160.000 -0.6685 0.0713 -1.0947 + 170.000 -0.3342 0.0427 -1.0947 + 180.000 0.0000 0.0427 -1.0947 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0427 -1.0947 + -170.000 0.3520 0.0427 -1.0947 + -160.000 0.7039 0.0744 -1.0947 + -150.000 0.9952 0.2405 -1.0947 + -140.000 0.7965 0.4453 -1.0947 + -130.000 0.6385 0.6648 -1.0947 + -120.000 0.4830 0.8740 -1.0947 + -110.000 0.3206 1.0489 -1.0947 + -100.000 0.1555 1.1699 -1.0947 + -90.000 0.0000 1.2239 -1.0947 + -80.000 -0.1555 1.1699 -1.0947 + -70.000 -0.3206 1.0489 -1.0947 + -60.000 -0.4830 0.8740 -1.0947 + -50.000 -0.6385 0.6648 -1.0947 + -40.000 -0.7965 0.4453 -1.0947 + -30.000 -0.9952 0.2405 -1.0947 + -20.000 -0.7566 0.1382 -1.0947 + -10.000 -0.6615 0.0454 -2.5749 + -7.000 -0.4812 0.0415 -1.7511 + -6.000 -0.3745 0.0410 -1.4789 + -5.000 -0.2649 0.0403 -1.2901 + -4.000 -0.1519 0.0399 -1.1074 + -3.000 -0.0361 0.0396 -0.9899 + -2.000 0.0806 0.0393 -1.0134 + -1.000 0.1980 0.0387 -1.0949 + 0.000 0.3153 0.0387 -1.1812 + 1.000 0.4305 0.0387 -1.2694 + 2.000 0.5438 0.0390 -1.3540 + 3.000 0.6538 0.0394 -1.4370 + 4.000 0.7567 0.0402 -1.5286 + 5.000 0.8514 0.0412 -1.6190 + 6.000 0.9493 0.0417 -1.7316 + 7.000 1.0402 0.0424 -1.8683 + 8.000 1.0816 0.0435 -2.0142 + 10.000 1.1457 0.0485 -2.2994 + 11.000 1.1887 0.0516 -2.5309 + 12.000 1.2299 0.0553 -2.8127 + 13.000 1.2688 0.0595 -3.1081 + 14.000 1.2973 0.0651 -3.3981 + 15.000 1.3297 0.0708 -3.7201 + 17.000 1.3841 0.0846 -4.4087 + 18.000 1.4065 0.0927 -4.7570 + 19.000 1.4248 0.1017 -5.1168 + 20.000 1.4340 0.1123 -5.4530 + 22.000 1.4727 0.1319 -6.2606 + 23.000 1.4802 0.1438 -6.6509 + 24.000 1.4856 0.1558 -7.0399 + 25.000 1.4882 0.1682 -7.4120 + 26.000 1.4872 0.1810 -7.7597 + 27.000 1.4803 0.1942 -8.0622 + 28.000 1.4702 0.2080 -8.3300 + 29.000 1.4581 0.2218 -8.5675 + 30.000 1.4218 0.2405 -8.1097 + 40.000 1.1378 0.4453 -1.0947 + 50.000 0.9121 0.6648 -1.0947 + 60.000 0.6900 0.8740 -1.0947 + 70.000 0.4579 1.0489 -1.0947 + 80.000 0.2222 1.1699 -1.0947 + 90.000 0.0000 1.2239 -1.0947 + 100.000 -0.1555 1.1699 -1.0947 + 110.000 -0.3206 1.0489 -1.0947 + 120.000 -0.4830 0.8740 -1.0947 + 130.000 -0.6385 0.6648 -1.0947 + 140.000 -0.7965 0.4453 -1.0947 + 150.000 -0.9952 0.2405 -1.0947 + 160.000 -0.7039 0.0744 -1.0947 + 170.000 -0.3520 0.0427 -1.0947 + 180.000 0.0000 0.0427 -1.0947 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0427 -1.0947 + -170.000 0.3392 0.0427 -1.0947 + -160.000 0.6784 0.0675 -1.0947 + -150.000 1.0176 0.2342 -1.0947 + -140.000 0.8101 0.4396 -1.0947 + -130.000 0.6466 0.6602 -1.0947 + -120.000 0.4873 0.8704 -1.0947 + -110.000 0.3224 1.0465 -1.0947 + -100.000 0.1559 1.1686 -1.0947 + -90.000 0.0000 1.2239 -1.0947 + -80.000 -0.1559 1.1686 -1.0947 + -70.000 -0.3224 1.0465 -1.0947 + -60.000 -0.4873 0.8704 -1.0947 + -50.000 -0.6466 0.6602 -1.0947 + -40.000 -0.8101 0.4396 -1.0947 + -30.000 -1.0176 0.2342 -1.0947 + -20.000 -0.7448 0.1396 -1.0947 + -10.000 -0.6743 0.0450 -2.6018 + -9.000 -0.6556 0.0432 -2.3780 + -8.000 -0.5837 0.0419 -2.0858 + -6.000 -0.3744 0.0409 -1.4766 + -5.000 -0.2648 0.0402 -1.2898 + -4.000 -0.1518 0.0397 -1.1073 + -3.000 -0.0353 0.0395 -0.9902 + -2.000 0.0816 0.0392 -1.0140 + -1.000 0.1984 0.0387 -1.0951 + 0.000 0.3163 0.0386 -1.1820 + 1.000 0.4294 0.0388 -1.2695 + 2.000 0.5437 0.0390 -1.3533 + 3.000 0.6525 0.0395 -1.4353 + 5.000 0.8543 0.0411 -1.6221 + 6.000 0.9522 0.0417 -1.7348 + 7.000 1.0473 0.0422 -1.8753 + 8.000 1.0856 0.0434 -2.0185 + 11.000 1.1998 0.0511 -2.5530 + 12.000 1.2410 0.0546 -2.8360 + 14.000 1.3174 0.0635 -3.4485 + 16.000 1.3700 0.0763 -4.0931 + 18.000 1.4171 0.0916 -4.7936 + 21.000 1.4744 0.1193 -5.9336 + 22.000 1.4840 0.1304 -6.3121 + 23.000 1.4926 0.1420 -6.7143 + 24.000 1.4971 0.1541 -7.1018 + 25.000 1.4986 0.1667 -7.4716 + 26.000 1.4943 0.1799 -7.8035 + 27.000 1.4875 0.1932 -8.1091 + 28.000 1.4786 0.2066 -8.3887 + 29.000 1.4676 0.2203 -8.6380 + 30.000 1.4537 0.2342 -8.8479 + 40.000 1.1573 0.4396 -1.0947 + 50.000 0.9237 0.6602 -1.0947 + 60.000 0.6962 0.8704 -1.0947 + 70.000 0.4606 1.0465 -1.0947 + 80.000 0.2228 1.1686 -1.0947 + 90.000 0.0000 1.2239 -1.0947 + 100.000 -0.1559 1.1686 -1.0947 + 110.000 -0.3224 1.0465 -1.0947 + 120.000 -0.4873 0.8704 -1.0947 + 130.000 -0.6466 0.6602 -1.0947 + 140.000 -0.8101 0.4396 -1.0947 + 150.000 -1.0176 0.2342 -1.0947 + 160.000 -0.6784 0.0675 -1.0947 + 170.000 -0.3392 0.0427 -1.0947 + 180.000 0.0000 0.0427 -1.0947 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0276_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0276_coords.txt new file mode 100644 index 00000000..c2553444 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0276_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0276 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.024017 + 0.027091 0.050261 + 0.060263 0.077244 + 0.105430 0.102168 + 0.161359 0.123903 + 0.226526 0.140948 + 0.299152 0.151887 + 0.377257 0.154763 + 0.458710 0.148989 + 0.541290 0.136081 + 0.622743 0.118030 + 0.700848 0.097075 + 0.773474 0.075618 + 0.838641 0.055666 + 0.894570 0.038477 + 0.939737 0.024535 + 0.972909 0.013769 + 0.993181 0.005721 + 1.000000 0.000000 + 0.993181 -0.003319 + 0.972909 -0.006500 + 0.939737 -0.011272 + 0.894570 -0.018909 + 0.838641 -0.030129 + 0.773474 -0.044953 + 0.700848 -0.062630 + 0.622743 -0.081432 + 0.541290 -0.099052 + 0.458710 -0.113095 + 0.377257 -0.121217 + 0.299152 -0.121652 + 0.226526 -0.115046 + 0.161359 -0.102964 + 0.105430 -0.086660 + 0.060263 -0.067057 + 0.027091 -0.044998 + 0.006819 -0.021867 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0329.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0329.dat new file mode 100644 index 00000000..b975b05e --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0329.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0329 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0329_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0440 -1.2342 + -170.000 0.2755 0.0440 -1.2342 + -160.000 0.5509 0.0975 -1.2342 + -150.000 0.8264 0.2495 -1.2342 + -140.000 0.6797 0.4368 -1.2342 + -130.000 0.5573 0.6371 -1.2342 + -120.000 0.4292 0.8274 -1.2342 + -110.000 0.2891 0.9854 -1.2342 + -100.000 0.1421 1.0931 -1.2342 + -90.000 0.0000 1.1387 -1.2342 + -80.000 -0.1421 1.0931 -1.2342 + -70.000 -0.2891 0.9854 -1.2342 + -60.000 -0.4292 0.8274 -1.2342 + -50.000 -0.5573 0.6371 -1.2342 + -40.000 -0.6797 0.4368 -1.2342 + -30.000 -0.8264 0.2495 -1.2342 + -20.000 -0.5988 0.1504 -1.2342 + -10.000 -0.5303 0.0513 -2.4401 + -9.000 -0.5035 0.0484 -2.2366 + -8.000 -0.4769 0.0461 -2.0401 + -7.000 -0.4294 0.0449 -1.8137 + -6.000 -0.3453 0.0440 -1.5940 + -5.000 -0.2498 0.0433 -1.4194 + -4.000 -0.1500 0.0427 -1.2559 + -3.000 -0.0483 0.0418 -1.1508 + -2.000 0.0592 0.0417 -1.1501 + -1.000 0.1663 0.0416 -1.2243 + 0.000 0.2730 0.0417 -1.3028 + 1.000 0.3803 0.0417 -1.3838 + 2.000 0.4859 0.0418 -1.4645 + 3.000 0.5895 0.0420 -1.5483 + 4.000 0.6893 0.0424 -1.6326 + 5.000 0.7876 0.0427 -1.7252 + 6.000 0.8679 0.0437 -1.8212 + 7.000 0.9002 0.0452 -1.8936 + 8.000 0.9294 0.0472 -2.0052 + 9.000 0.9652 0.0498 -2.1398 + 10.000 1.0023 0.0528 -2.2804 + 11.000 1.0093 0.0580 -2.3844 + 12.000 1.0356 0.0628 -2.6060 + 13.000 1.0441 0.0697 -2.7946 + 14.000 1.0672 0.0761 -3.0285 + 15.000 1.0835 0.0837 -3.2567 + 16.000 1.1087 0.0911 -3.5261 + 17.000 1.1306 0.0991 -3.8034 + 18.000 1.1510 0.1080 -4.0965 + 19.000 1.1700 0.1172 -4.3899 + 20.000 1.1865 0.1272 -4.6928 + 21.000 1.2019 0.1375 -5.0028 + 22.000 1.2192 0.1473 -5.3358 + 23.000 1.2267 0.1588 -5.6377 + 24.000 1.2326 0.1704 -5.9354 + 25.000 1.2334 0.1825 -6.2163 + 26.000 1.2292 0.1953 -6.4566 + 28.000 1.2072 0.2216 -6.8060 + 29.000 1.1908 0.2363 -6.8946 + 30.000 1.1805 0.2495 -7.0038 + 40.000 0.9711 0.4368 -1.2342 + 50.000 0.7961 0.6371 -1.2342 + 60.000 0.6131 0.8274 -1.2342 + 70.000 0.4130 0.9854 -1.2342 + 80.000 0.2031 1.0931 -1.2342 + 90.000 0.0000 1.1387 -1.2342 + 100.000 -0.1421 1.0931 -1.2342 + 110.000 -0.2891 0.9854 -1.2342 + 120.000 -0.4292 0.8274 -1.2342 + 130.000 -0.5573 0.6371 -1.2342 + 140.000 -0.6797 0.4368 -1.2342 + 150.000 -0.8264 0.2495 -1.2342 + 160.000 -0.5509 0.0975 -1.2342 + 170.000 -0.2755 0.0440 -1.2342 + 180.000 0.0000 0.0440 -1.2342 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0873 -1.2342 + -170.000 0.2887 0.0873 -1.2342 + -160.000 0.5775 0.1303 -1.2342 + -150.000 0.8662 0.2831 -1.2342 + -140.000 0.7040 0.4714 -1.2342 + -130.000 0.5716 0.6732 -1.2342 + -120.000 0.4369 0.8650 -1.2342 + -110.000 0.2924 1.0248 -1.2342 + -100.000 0.1429 1.1345 -1.2342 + -90.000 0.0000 1.1821 -1.2342 + -80.000 -0.1429 1.1345 -1.2342 + -70.000 -0.2924 1.0248 -1.2342 + -60.000 -0.4369 0.8650 -1.2342 + -50.000 -0.5716 0.6732 -1.2342 + -40.000 -0.7040 0.4714 -1.2342 + -30.000 -0.8662 0.2831 -1.2342 + -20.000 -0.6329 0.1877 -1.2342 + -10.000 -0.5710 0.0922 -2.5258 + -9.000 -0.5294 0.0901 -2.2859 + -8.000 -0.5122 0.0883 -2.1009 + -7.000 -0.4370 0.0873 -1.8275 + -6.000 -0.3452 0.0866 -1.5943 + -5.000 -0.2481 0.0860 -1.4179 + -4.000 -0.1447 0.0855 -1.2505 + -3.000 -0.0401 0.0849 -1.1451 + -1.000 0.1750 0.0842 -1.2294 + 0.000 0.2837 0.0841 -1.3095 + 1.000 0.3905 0.0843 -1.3903 + 2.000 0.4984 0.0843 -1.4727 + 5.000 0.7926 0.0858 -1.7277 + 6.000 0.8625 0.0870 -1.8182 + 7.000 0.9104 0.0881 -1.9017 + 9.000 1.0001 0.0914 -2.1829 + 10.000 1.0176 0.0951 -2.3002 + 11.000 1.0483 0.0988 -2.4594 + 12.000 1.0619 0.1042 -2.6613 + 13.000 1.0871 0.1095 -2.8912 + 14.000 1.1125 0.1153 -3.1432 + 15.000 1.1426 0.1213 -3.4165 + 16.000 1.1668 0.1283 -3.6993 + 17.000 1.1917 0.1356 -4.0066 + 18.000 1.2125 0.1438 -4.3127 + 19.000 1.2331 0.1524 -4.6272 + 20.000 1.2462 0.1624 -4.9387 + 21.000 1.2599 0.1726 -5.2566 + 22.000 1.2717 0.1833 -5.5870 + 23.000 1.2757 0.1949 -5.8874 + 24.000 1.2879 0.2053 -6.2523 + 25.000 1.2885 0.2173 -6.5549 + 26.000 1.2891 0.2291 -6.8508 + 27.000 1.2857 0.2414 -7.1130 + 28.000 1.2786 0.2541 -7.3364 + 29.000 1.2520 0.2694 -7.3962 + 30.000 1.2375 0.2831 -7.5119 + 40.000 1.0057 0.4714 -1.2342 + 50.000 0.8166 0.6732 -1.2342 + 60.000 0.6240 0.8650 -1.2342 + 70.000 0.4177 1.0248 -1.2342 + 80.000 0.2042 1.1345 -1.2342 + 90.000 0.0000 1.1821 -1.2342 + 100.000 -0.1429 1.1345 -1.2342 + 110.000 -0.2924 1.0248 -1.2342 + 120.000 -0.4369 0.8650 -1.2342 + 130.000 -0.5716 0.6732 -1.2342 + 140.000 -0.7040 0.4714 -1.2342 + 150.000 -0.8662 0.2831 -1.2342 + 160.000 -0.5775 0.1303 -1.2342 + 170.000 -0.2887 0.0873 -1.2342 + 180.000 0.0000 0.0873 -1.2342 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0908 -1.2342 + -170.000 0.2995 0.0908 -1.2342 + -160.000 0.5990 0.1258 -1.2342 + -150.000 0.8984 0.2793 -1.2342 + -140.000 0.7236 0.4684 -1.2342 + -130.000 0.5832 0.6712 -1.2342 + -120.000 0.4430 0.8643 -1.2342 + -110.000 0.2951 1.0254 -1.2342 + -100.000 0.1436 1.1366 -1.2342 + -90.000 0.0000 1.1856 -1.2342 + -80.000 -0.1436 1.1366 -1.2342 + -70.000 -0.2951 1.0254 -1.2342 + -60.000 -0.4430 0.8643 -1.2342 + -50.000 -0.5832 0.6712 -1.2342 + -40.000 -0.7236 0.4684 -1.2342 + -30.000 -0.8984 0.2793 -1.2342 + -20.000 -0.6573 0.1869 -1.2342 + -10.000 -0.5945 0.0944 -2.5752 + -9.000 -0.5572 0.0925 -2.3371 + -8.000 -0.5216 0.0912 -2.1174 + -7.000 -0.4385 0.0904 -1.8300 + -6.000 -0.3467 0.0897 -1.5966 + -5.000 -0.2462 0.0891 -1.4158 + -4.000 -0.1422 0.0888 -1.2476 + -3.000 -0.0370 0.0883 -1.1433 + -2.000 0.0700 0.0876 -1.1563 + -1.000 0.1788 0.0874 -1.2317 + 0.000 0.2873 0.0874 -1.3116 + 1.000 0.3964 0.0874 -1.3941 + 2.000 0.5017 0.0876 -1.4750 + 4.000 0.7033 0.0884 -1.6456 + 5.000 0.7898 0.0894 -1.7274 + 6.000 0.8653 0.0904 -1.8141 + 7.000 0.9223 0.0912 -1.9135 + 8.000 0.9769 0.0923 -2.0568 + 9.000 1.0075 0.0945 -2.1916 + 10.000 1.0397 0.0974 -2.3303 + 11.000 1.0607 0.1014 -2.4839 + 12.000 1.0873 0.1058 -2.7148 + 13.000 1.1111 0.1110 -2.9461 + 14.000 1.1448 0.1161 -3.2245 + 15.000 1.1715 0.1221 -3.4976 + 16.000 1.1977 0.1287 -3.7910 + 17.000 1.2217 0.1359 -4.1053 + 19.000 1.2606 0.1526 -4.7329 + 20.000 1.2896 0.1602 -5.1156 + 21.000 1.3005 0.1704 -5.4311 + 22.000 1.3073 0.1816 -5.7547 + 23.000 1.3114 0.1931 -6.0712 + 24.000 1.3170 0.2045 -6.4155 + 25.000 1.3194 0.2162 -6.7394 + 26.000 1.3171 0.2283 -7.0302 + 27.000 1.3109 0.2409 -7.2856 + 28.000 1.3036 0.2535 -7.5195 + 29.000 1.2948 0.2662 -7.7268 + 30.000 1.2835 0.2793 -7.8953 + 40.000 1.0337 0.4684 -1.2342 + 50.000 0.8331 0.6712 -1.2342 + 60.000 0.6329 0.8643 -1.2342 + 70.000 0.4216 1.0254 -1.2342 + 80.000 0.2052 1.1366 -1.2342 + 90.000 0.0000 1.1856 -1.2342 + 100.000 -0.1436 1.1366 -1.2342 + 110.000 -0.2951 1.0254 -1.2342 + 120.000 -0.4430 0.8643 -1.2342 + 130.000 -0.5832 0.6712 -1.2342 + 140.000 -0.7236 0.4684 -1.2342 + 150.000 -0.8984 0.2793 -1.2342 + 160.000 -0.5990 0.1258 -1.2342 + 170.000 -0.2995 0.0908 -1.2342 + 180.000 0.0000 0.0908 -1.2342 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0908 -1.2342 + -170.000 0.3589 0.0908 -1.2342 + -160.000 0.7178 0.1399 -1.2342 + -150.000 0.8463 0.2923 -1.2342 + -140.000 0.6918 0.4800 -1.2342 + -130.000 0.5644 0.6809 -1.2342 + -120.000 0.4330 0.8718 -1.2342 + -110.000 0.2907 1.0306 -1.2342 + -100.000 0.1426 1.1392 -1.2342 + -90.000 0.0000 1.1856 -1.2342 + -80.000 -0.1426 1.1392 -1.2342 + -70.000 -0.2907 1.0306 -1.2342 + -60.000 -0.4330 0.8718 -1.2342 + -50.000 -0.5644 0.6809 -1.2342 + -40.000 -0.6918 0.4800 -1.2342 + -30.000 -0.8463 0.2923 -1.2342 + -20.000 -0.7416 0.1764 -1.2342 + -10.000 -0.6035 0.0940 -2.6010 + -9.000 -0.5784 0.0917 -2.3771 + -8.000 -0.5289 0.0908 -2.1303 + -5.000 -0.2459 0.0889 -1.4153 + -4.000 -0.1417 0.0885 -1.2471 + -3.000 -0.0350 0.0882 -1.1334 + -2.000 0.0720 0.0876 -1.1574 + -1.000 0.1806 0.0873 -1.2325 + 0.000 0.2903 0.0872 -1.3135 + 1.000 0.3977 0.0872 -1.3948 + 2.000 0.5029 0.0874 -1.4763 + 3.000 0.6065 0.0878 -1.5602 + 4.000 0.7026 0.0885 -1.6371 + 6.000 0.8709 0.0903 -1.8131 + 7.000 0.9390 0.0909 -1.9283 + 8.000 0.9903 0.0919 -2.0725 + 9.000 1.0182 0.0941 -2.2052 + 11.000 1.0718 0.1008 -2.5055 + 12.000 1.1056 0.1046 -2.7534 + 13.000 1.1409 0.1088 -3.0171 + 15.000 1.2029 0.1193 -3.5854 + 16.000 1.2292 0.1256 -3.8876 + 17.000 1.2559 0.1323 -4.2180 + 18.000 1.2741 0.1402 -4.5271 + 19.000 1.2946 0.1485 -4.8636 + 20.000 1.3084 0.1579 -5.1912 + 22.000 1.3238 0.1794 -5.8311 + 25.000 1.3343 0.2140 -6.8274 + 26.000 1.3330 0.2260 -7.1297 + 30.000 1.2089 0.2923 -5.8073 + 40.000 0.9884 0.4800 -1.2342 + 50.000 0.8063 0.6809 -1.2342 + 60.000 0.6186 0.8718 -1.2342 + 70.000 0.4154 1.0306 -1.2342 + 80.000 0.2037 1.1392 -1.2342 + 90.000 0.0000 1.1856 -1.2342 + 100.000 -0.1426 1.1392 -1.2342 + 110.000 -0.2907 1.0306 -1.2342 + 120.000 -0.4330 0.8718 -1.2342 + 130.000 -0.5644 0.6809 -1.2342 + 140.000 -0.6918 0.4800 -1.2342 + 150.000 -0.8463 0.2923 -1.2342 + 160.000 -0.7178 0.1399 -1.2342 + 170.000 -0.3589 0.0908 -1.2342 + 180.000 0.0000 0.0908 -1.2342 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0908 -1.2342 + -170.000 0.3097 0.0908 -1.2342 + -160.000 0.6195 0.1173 -1.2342 + -150.000 0.9292 0.2715 -1.2342 + -140.000 0.7423 0.4615 -1.2342 + -130.000 0.5943 0.6655 -1.2342 + -120.000 0.4490 0.8598 -1.2342 + -110.000 0.2976 1.0223 -1.2342 + -100.000 0.1443 1.1350 -1.2342 + -90.000 0.0000 1.1856 -1.2342 + -80.000 -0.1443 1.1350 -1.2342 + -70.000 -0.2976 1.0223 -1.2342 + -60.000 -0.4490 0.8598 -1.2342 + -50.000 -0.5943 0.6655 -1.2342 + -40.000 -0.7423 0.4615 -1.2342 + -30.000 -0.9292 0.2715 -1.2342 + -20.000 -0.6751 0.1827 -1.2342 + -10.000 -0.6013 0.0939 -2.5800 + -9.000 -0.6049 0.0913 -2.4300 + -8.000 -0.5351 0.0905 -2.1415 + -6.000 -0.3479 0.0892 -1.6003 + -4.000 -0.1409 0.0883 -1.2463 + -3.000 -0.0343 0.0881 -1.1345 + -2.000 0.0733 0.0876 -1.1581 + -1.000 0.1825 0.0872 -1.2337 + 0.000 0.2915 0.0871 -1.3142 + 1.000 0.3984 0.0872 -1.3953 + 2.000 0.5032 0.0874 -1.4781 + 4.000 0.7008 0.0886 -1.6330 + 5.000 0.7884 0.0895 -1.7176 + 6.000 0.8737 0.0902 -1.8187 + 7.000 0.9573 0.0907 -1.9445 + 8.000 0.9963 0.0918 -2.0792 + 9.000 1.0325 0.0935 -2.2235 + 10.000 1.0483 0.0969 -2.3279 + 11.000 1.0905 0.0997 -2.5427 + 12.000 1.1219 0.1035 -2.7879 + 13.000 1.1561 0.1078 -3.0531 + 14.000 1.1901 0.1124 -3.3382 + 16.000 1.2477 0.1239 -3.9451 + 17.000 1.2697 0.1309 -4.2627 + 18.000 1.2918 0.1384 -4.5882 + 19.000 1.3089 0.1468 -4.9179 + 20.000 1.3218 0.1562 -5.2450 + 21.000 1.3285 0.1667 -5.5530 + 24.000 1.3627 0.1976 -6.6668 + 25.000 1.3660 0.2090 -7.0127 + 26.000 1.3664 0.2208 -7.3375 + 27.000 1.3628 0.2327 -7.6317 + 28.000 1.3542 0.2452 -7.8817 + 29.000 1.3417 0.2583 -8.0880 + 30.000 1.3275 0.2715 -8.2610 + 40.000 1.0605 0.4615 -1.2342 + 50.000 0.8489 0.6655 -1.2342 + 60.000 0.6414 0.8598 -1.2342 + 70.000 0.4252 1.0223 -1.2342 + 80.000 0.2061 1.1350 -1.2342 + 90.000 0.0000 1.1856 -1.2342 + 100.000 -0.1443 1.1350 -1.2342 + 110.000 -0.2976 1.0223 -1.2342 + 120.000 -0.4490 0.8598 -1.2342 + 130.000 -0.5943 0.6655 -1.2342 + 140.000 -0.7423 0.4615 -1.2342 + 150.000 -0.9292 0.2715 -1.2342 + 160.000 -0.6195 0.1173 -1.2342 + 170.000 -0.3097 0.0908 -1.2342 + 180.000 0.0000 0.0908 -1.2342 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0908 -1.2342 + -170.000 0.3262 0.0908 -1.2342 + -160.000 0.6524 0.1202 -1.2342 + -150.000 0.9224 0.2741 -1.2342 + -140.000 0.7382 0.4639 -1.2342 + -130.000 0.5918 0.6674 -1.2342 + -120.000 0.4476 0.8613 -1.2342 + -110.000 0.2971 1.0234 -1.2342 + -100.000 0.1441 1.1355 -1.2342 + -90.000 0.0000 1.1856 -1.2342 + -80.000 -0.1441 1.1355 -1.2342 + -70.000 -0.2971 1.0234 -1.2342 + -60.000 -0.4476 0.8613 -1.2342 + -50.000 -0.5918 0.6674 -1.2342 + -40.000 -0.7382 0.4639 -1.2342 + -30.000 -0.9224 0.2741 -1.2342 + -20.000 -0.7012 0.1794 -1.2342 + -10.000 -0.6131 0.0934 -2.6061 + -7.000 -0.4460 0.0897 -1.8425 + -6.000 -0.3471 0.0892 -1.5903 + -5.000 -0.2455 0.0886 -1.4153 + -4.000 -0.1408 0.0882 -1.2460 + -3.000 -0.0335 0.0880 -1.1370 + -2.000 0.0747 0.0876 -1.1588 + -1.000 0.1835 0.0871 -1.2344 + 0.000 0.2922 0.0871 -1.3144 + 1.000 0.3990 0.0871 -1.3960 + 2.000 0.5040 0.0874 -1.4745 + 3.000 0.6059 0.0878 -1.5514 + 4.000 0.7013 0.0885 -1.6363 + 5.000 0.7890 0.0894 -1.7201 + 6.000 0.8798 0.0899 -1.8244 + 7.000 0.9640 0.0905 -1.9511 + 8.000 1.0024 0.0916 -2.0864 + 10.000 1.0619 0.0962 -2.3507 + 11.000 1.1017 0.0991 -2.5653 + 12.000 1.1399 0.1025 -2.8264 + 13.000 1.1759 0.1063 -3.1002 + 14.000 1.2023 0.1116 -3.3690 + 15.000 1.2323 0.1168 -3.6674 + 17.000 1.2828 0.1297 -4.3055 + 18.000 1.3035 0.1372 -4.6284 + 19.000 1.3205 0.1455 -4.9619 + 20.000 1.3290 0.1553 -5.2735 + 22.000 1.3649 0.1735 -6.0219 + 23.000 1.3718 0.1845 -6.3836 + 24.000 1.3769 0.1956 -6.7442 + 25.000 1.3793 0.2072 -7.0890 + 26.000 1.3784 0.2190 -7.4113 + 27.000 1.3719 0.2313 -7.6916 + 28.000 1.3626 0.2440 -7.9398 + 29.000 1.3514 0.2568 -8.1599 + 30.000 1.3177 0.2741 -7.7356 + 40.000 1.0545 0.4639 -1.2342 + 50.000 0.8454 0.6674 -1.2342 + 60.000 0.6395 0.8613 -1.2342 + 70.000 0.4244 1.0234 -1.2342 + 80.000 0.2059 1.1355 -1.2342 + 90.000 0.0000 1.1856 -1.2342 + 100.000 -0.1441 1.1355 -1.2342 + 110.000 -0.2971 1.0234 -1.2342 + 120.000 -0.4476 0.8613 -1.2342 + 130.000 -0.5918 0.6674 -1.2342 + 140.000 -0.7382 0.4639 -1.2342 + 150.000 -0.9224 0.2741 -1.2342 + 160.000 -0.6524 0.1202 -1.2342 + 170.000 -0.3262 0.0908 -1.2342 + 180.000 0.0000 0.0908 -1.2342 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0908 -1.2342 + -170.000 0.3144 0.0908 -1.2342 + -160.000 0.6287 0.1138 -1.2342 + -150.000 0.9431 0.2683 -1.2342 + -140.000 0.7508 0.4587 -1.2342 + -130.000 0.5992 0.6631 -1.2342 + -120.000 0.4516 0.8579 -1.2342 + -110.000 0.2988 1.0211 -1.2342 + -100.000 0.1445 1.1343 -1.2342 + -90.000 0.0000 1.1856 -1.2342 + -80.000 -0.1445 1.1343 -1.2342 + -70.000 -0.2988 1.0211 -1.2342 + -60.000 -0.4516 0.8579 -1.2342 + -50.000 -0.5992 0.6631 -1.2342 + -40.000 -0.7508 0.4587 -1.2342 + -30.000 -0.9431 0.2683 -1.2342 + -20.000 -0.6902 0.1806 -1.2342 + -10.000 -0.6249 0.0929 -2.6310 + -9.000 -0.6076 0.0912 -2.4236 + -8.000 -0.5409 0.0901 -2.1527 + -6.000 -0.3470 0.0891 -1.5882 + -5.000 -0.2454 0.0885 -1.4150 + -4.000 -0.1407 0.0881 -1.2459 + -3.000 -0.0328 0.0879 -1.1374 + -2.000 0.0757 0.0875 -1.1594 + -1.000 0.1839 0.0871 -1.2346 + 0.000 0.2931 0.0870 -1.3151 + 1.000 0.3980 0.0872 -1.3962 + 2.000 0.5039 0.0874 -1.4738 + 3.000 0.6047 0.0879 -1.5498 + 5.000 0.7918 0.0893 -1.7230 + 6.000 0.8825 0.0899 -1.8274 + 7.000 0.9707 0.0904 -1.9577 + 8.000 1.0061 0.0914 -2.0904 + 11.000 1.1120 0.0986 -2.5857 + 12.000 1.1501 0.1018 -2.8480 + 14.000 1.2210 0.1100 -3.4157 + 16.000 1.2697 0.1220 -4.0131 + 18.000 1.3134 0.1361 -4.6623 + 21.000 1.3665 0.1618 -5.7189 + 22.000 1.3754 0.1721 -6.0696 + 23.000 1.3833 0.1829 -6.4424 + 24.000 1.3875 0.1941 -6.8016 + 25.000 1.3889 0.2058 -7.1442 + 26.000 1.3849 0.2179 -7.4518 + 27.000 1.3786 0.2303 -7.7351 + 28.000 1.3703 0.2427 -7.9942 + 29.000 1.3602 0.2554 -8.2252 + 30.000 1.3473 0.2683 -8.4198 + 40.000 1.0725 0.4587 -1.2342 + 50.000 0.8561 0.6631 -1.2342 + 60.000 0.6452 0.8579 -1.2342 + 70.000 0.4269 1.0211 -1.2342 + 80.000 0.2065 1.1343 -1.2342 + 90.000 0.0000 1.1856 -1.2342 + 100.000 -0.1445 1.1343 -1.2342 + 110.000 -0.2988 1.0211 -1.2342 + 120.000 -0.4516 0.8579 -1.2342 + 130.000 -0.5992 0.6631 -1.2342 + 140.000 -0.7508 0.4587 -1.2342 + 150.000 -0.9431 0.2683 -1.2342 + 160.000 -0.6287 0.1138 -1.2342 + 170.000 -0.3144 0.0908 -1.2342 + 180.000 0.0000 0.0908 -1.2342 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0329_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0329_coords.txt new file mode 100644 index 00000000..00d5ebe9 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0329_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0329 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.028484 + 0.027091 0.058831 + 0.060263 0.089532 + 0.105430 0.117836 + 0.161359 0.142554 + 0.226526 0.162174 + 0.299152 0.175281 + 0.377257 0.179988 + 0.458710 0.175693 + 0.541290 0.163772 + 0.622743 0.146064 + 0.700848 0.124660 + 0.773474 0.101839 + 0.838641 0.079535 + 0.894570 0.059015 + 0.939737 0.040853 + 0.972909 0.025130 + 0.993181 0.011587 + 1.000000 0.000000 + 0.993181 -0.009368 + 0.972909 -0.018416 + 0.939737 -0.028604 + 0.894570 -0.040942 + 0.838641 -0.055950 + 0.773474 -0.073518 + 0.700848 -0.092848 + 0.622743 -0.112264 + 0.541290 -0.129574 + 0.458710 -0.142543 + 0.377257 -0.149007 + 0.299152 -0.147357 + 0.226526 -0.138252 + 0.161359 -0.123216 + 0.105430 -0.103514 + 0.060263 -0.080124 + 0.027091 -0.053971 + 0.006819 -0.026499 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0444.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0444.dat new file mode 100644 index 00000000..1957eb43 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0444.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0444 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0444_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.0878 -1.5368 + -170.000 0.2283 0.0878 -1.5368 + -160.000 0.4565 0.1322 -1.5368 + -150.000 0.6848 0.2582 -1.5368 + -140.000 0.5632 0.4133 -1.5368 + -130.000 0.4618 0.5793 -1.5368 + -120.000 0.3556 0.7370 -1.5368 + -110.000 0.2396 0.8679 -1.5368 + -100.000 0.1178 0.9572 -1.5368 + -90.000 0.0000 0.9950 -1.5368 + -80.000 -0.1178 0.9572 -1.5368 + -70.000 -0.2396 0.8679 -1.5368 + -60.000 -0.3556 0.7370 -1.5368 + -50.000 -0.4618 0.5793 -1.5368 + -40.000 -0.5632 0.4133 -1.5368 + -30.000 -0.6848 0.2582 -1.5368 + -20.000 -0.4962 0.1761 -1.5368 + -10.000 -0.4394 0.0939 -2.5360 + -9.000 -0.4172 0.0915 -2.3675 + -8.000 -0.3951 0.0896 -2.2046 + -7.000 -0.3558 0.0886 -2.0171 + -6.000 -0.2861 0.0879 -1.8350 + -5.000 -0.2070 0.0873 -1.6903 + -4.000 -0.1243 0.0868 -1.5548 + -3.000 -0.0400 0.0861 -1.4677 + -2.000 0.0491 0.0859 -1.4671 + -1.000 0.1378 0.0859 -1.5286 + 0.000 0.2262 0.0859 -1.5937 + 1.000 0.3151 0.0859 -1.6608 + 2.000 0.4026 0.0861 -1.7276 + 3.000 0.4885 0.0862 -1.7971 + 4.000 0.5711 0.0865 -1.8669 + 5.000 0.6526 0.0868 -1.9437 + 6.000 0.7191 0.0876 -2.0232 + 7.000 0.7459 0.0889 -2.0832 + 8.000 0.7701 0.0905 -2.1757 + 9.000 0.7998 0.0927 -2.2872 + 10.000 0.8305 0.0952 -2.4037 + 11.000 0.8363 0.0995 -2.4899 + 12.000 0.8581 0.1034 -2.6735 + 13.000 0.8652 0.1092 -2.8298 + 14.000 0.8843 0.1145 -3.0236 + 15.000 0.8978 0.1208 -3.2127 + 16.000 0.9186 0.1269 -3.4359 + 17.000 0.9369 0.1336 -3.6657 + 18.000 0.9538 0.1409 -3.9085 + 19.000 0.9695 0.1486 -4.1517 + 20.000 0.9832 0.1568 -4.4027 + 21.000 0.9959 0.1653 -4.6596 + 22.000 1.0102 0.1735 -4.9355 + 23.000 1.0165 0.1830 -5.1857 + 24.000 1.0214 0.1926 -5.4324 + 25.000 1.0220 0.2026 -5.6651 + 26.000 1.0185 0.2132 -5.8642 + 28.000 1.0003 0.2350 -6.1537 + 29.000 0.9868 0.2472 -6.2271 + 30.000 0.9782 0.2582 -6.3176 + 40.000 0.8047 0.4133 -1.5368 + 50.000 0.6597 0.5793 -1.5368 + 60.000 0.5080 0.7370 -1.5368 + 70.000 0.3422 0.8679 -1.5368 + 80.000 0.1683 0.9572 -1.5368 + 90.000 0.0000 0.9950 -1.5368 + 100.000 -0.1178 0.9572 -1.5368 + 110.000 -0.2396 0.8679 -1.5368 + 120.000 -0.3556 0.7370 -1.5368 + 130.000 -0.4618 0.5793 -1.5368 + 140.000 -0.5632 0.4133 -1.5368 + 150.000 -0.6848 0.2582 -1.5368 + 160.000 -0.4565 0.1322 -1.5368 + 170.000 -0.2283 0.0878 -1.5368 + 180.000 0.0000 0.0878 -1.5368 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.1872 -1.5368 + -170.000 0.2392 0.1872 -1.5368 + -160.000 0.4785 0.2228 -1.5368 + -150.000 0.7178 0.3494 -1.5368 + -140.000 0.5834 0.5055 -1.5368 + -130.000 0.4736 0.6726 -1.5368 + -120.000 0.3620 0.8316 -1.5368 + -110.000 0.2423 0.9640 -1.5368 + -100.000 0.1184 1.0549 -1.5368 + -90.000 0.0000 1.0943 -1.5368 + -80.000 -0.1184 1.0549 -1.5368 + -70.000 -0.2423 0.9640 -1.5368 + -60.000 -0.3620 0.8316 -1.5368 + -50.000 -0.4736 0.6726 -1.5368 + -40.000 -0.5834 0.5055 -1.5368 + -30.000 -0.7178 0.3494 -1.5368 + -20.000 -0.5245 0.2703 -1.5368 + -10.000 -0.4731 0.1913 -2.6071 + -9.000 -0.4387 0.1895 -2.4083 + -8.000 -0.4244 0.1880 -2.2550 + -7.000 -0.3621 0.1872 -2.0285 + -6.000 -0.2860 0.1866 -1.8352 + -5.000 -0.2056 0.1861 -1.6890 + -4.000 -0.1199 0.1857 -1.5503 + -3.000 -0.0332 0.1852 -1.4630 + -1.000 0.1450 0.1846 -1.5328 + 0.000 0.2351 0.1845 -1.5992 + 1.000 0.3236 0.1847 -1.6662 + 2.000 0.4130 0.1847 -1.7344 + 5.000 0.6567 0.1859 -1.9457 + 6.000 0.7147 0.1869 -2.0208 + 7.000 0.7543 0.1878 -2.0899 + 9.000 0.8287 0.1906 -2.3229 + 10.000 0.8432 0.1936 -2.4202 + 11.000 0.8686 0.1967 -2.5521 + 12.000 0.8799 0.2011 -2.7194 + 13.000 0.9008 0.2055 -2.9099 + 14.000 0.9219 0.2103 -3.1187 + 15.000 0.9467 0.2153 -3.3452 + 16.000 0.9669 0.2211 -3.5794 + 17.000 0.9875 0.2272 -3.8341 + 18.000 1.0047 0.2340 -4.0877 + 19.000 1.0217 0.2411 -4.3483 + 20.000 1.0326 0.2494 -4.6065 + 21.000 1.0440 0.2578 -4.8698 + 22.000 1.0538 0.2667 -5.1436 + 23.000 1.0571 0.2763 -5.3926 + 24.000 1.0672 0.2850 -5.6949 + 25.000 1.0677 0.2949 -5.9456 + 26.000 1.0682 0.3046 -6.1909 + 27.000 1.0653 0.3148 -6.4081 + 28.000 1.0595 0.3254 -6.5932 + 29.000 1.0375 0.3381 -6.6428 + 30.000 1.0254 0.3494 -6.7387 + 40.000 0.8333 0.5055 -1.5368 + 50.000 0.6766 0.6726 -1.5368 + 60.000 0.5171 0.8316 -1.5368 + 70.000 0.3461 0.9640 -1.5368 + 80.000 0.1692 1.0549 -1.5368 + 90.000 0.0000 1.0943 -1.5368 + 100.000 -0.1184 1.0549 -1.5368 + 110.000 -0.2423 0.9640 -1.5368 + 120.000 -0.3620 0.8316 -1.5368 + 130.000 -0.4736 0.6726 -1.5368 + 140.000 -0.5834 0.5055 -1.5368 + 150.000 -0.7178 0.3494 -1.5368 + 160.000 -0.4785 0.2228 -1.5368 + 170.000 -0.2392 0.1872 -1.5368 + 180.000 0.0000 0.1872 -1.5368 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.1952 -1.5368 + -170.000 0.2482 0.1952 -1.5368 + -160.000 0.4963 0.2242 -1.5368 + -150.000 0.7445 0.3514 -1.5368 + -140.000 0.5996 0.5081 -1.5368 + -130.000 0.4832 0.6762 -1.5368 + -120.000 0.3671 0.8361 -1.5368 + -110.000 0.2445 0.9697 -1.5368 + -100.000 0.1190 1.0618 -1.5368 + -90.000 0.0000 1.1024 -1.5368 + -80.000 -0.1190 1.0618 -1.5368 + -70.000 -0.2445 0.9697 -1.5368 + -60.000 -0.3671 0.8361 -1.5368 + -50.000 -0.4832 0.6762 -1.5368 + -40.000 -0.5996 0.5081 -1.5368 + -30.000 -0.7445 0.3514 -1.5368 + -20.000 -0.5447 0.2748 -1.5368 + -10.000 -0.4926 0.1982 -2.6480 + -9.000 -0.4617 0.1966 -2.4507 + -8.000 -0.4322 0.1956 -2.2686 + -7.000 -0.3634 0.1949 -2.0305 + -6.000 -0.2873 0.1943 -1.8371 + -5.000 -0.2040 0.1938 -1.6873 + -4.000 -0.1179 0.1935 -1.5480 + -3.000 -0.0307 0.1932 -1.4615 + -2.000 0.0580 0.1926 -1.4722 + -1.000 0.1481 0.1924 -1.5347 + 0.000 0.2381 0.1924 -1.6009 + 1.000 0.3285 0.1924 -1.6693 + 2.000 0.4157 0.1926 -1.7363 + 4.000 0.5828 0.1932 -1.8778 + 5.000 0.6545 0.1940 -1.9455 + 6.000 0.7170 0.1949 -2.0173 + 7.000 0.7642 0.1956 -2.0997 + 8.000 0.8095 0.1965 -2.2185 + 9.000 0.8348 0.1983 -2.3302 + 10.000 0.8615 0.2007 -2.4451 + 11.000 0.8789 0.2040 -2.5723 + 12.000 0.9009 0.2076 -2.7637 + 13.000 0.9207 0.2120 -2.9553 + 14.000 0.9486 0.2162 -3.1860 + 15.000 0.9707 0.2212 -3.4123 + 16.000 0.9925 0.2266 -3.6554 + 17.000 1.0124 0.2326 -3.9159 + 19.000 1.0445 0.2464 -4.4359 + 20.000 1.0686 0.2527 -4.7530 + 21.000 1.0776 0.2612 -5.0144 + 22.000 1.0832 0.2704 -5.2826 + 23.000 1.0866 0.2800 -5.5449 + 24.000 1.0913 0.2894 -5.8301 + 25.000 1.0933 0.2991 -6.0985 + 26.000 1.0914 0.3091 -6.3395 + 27.000 1.0862 0.3196 -6.5511 + 28.000 1.0802 0.3300 -6.7450 + 29.000 1.0729 0.3406 -6.9167 + 30.000 1.0635 0.3514 -7.0563 + 40.000 0.8565 0.5081 -1.5368 + 50.000 0.6903 0.6762 -1.5368 + 60.000 0.5245 0.8361 -1.5368 + 70.000 0.3493 0.9697 -1.5368 + 80.000 0.1700 1.0618 -1.5368 + 90.000 0.0000 1.1024 -1.5368 + 100.000 -0.1190 1.0618 -1.5368 + 110.000 -0.2445 0.9697 -1.5368 + 120.000 -0.3671 0.8361 -1.5368 + 130.000 -0.4832 0.6762 -1.5368 + 140.000 -0.5996 0.5081 -1.5368 + 150.000 -0.7445 0.3514 -1.5368 + 160.000 -0.4963 0.2242 -1.5368 + 170.000 -0.2482 0.1952 -1.5368 + 180.000 0.0000 0.1952 -1.5368 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.1952 -1.5368 + -170.000 0.2974 0.1952 -1.5368 + -160.000 0.5948 0.2359 -1.5368 + -150.000 0.7012 0.3622 -1.5368 + -140.000 0.5733 0.5177 -1.5368 + -130.000 0.4677 0.6842 -1.5368 + -120.000 0.3588 0.8424 -1.5368 + -110.000 0.2409 0.9739 -1.5368 + -100.000 0.1181 1.0639 -1.5368 + -90.000 0.0000 1.1024 -1.5368 + -80.000 -0.1181 1.0639 -1.5368 + -70.000 -0.2409 0.9739 -1.5368 + -60.000 -0.3588 0.8424 -1.5368 + -50.000 -0.4677 0.6842 -1.5368 + -40.000 -0.5733 0.5177 -1.5368 + -30.000 -0.7012 0.3622 -1.5368 + -20.000 -0.6145 0.2662 -1.5368 + -10.000 -0.5000 0.1978 -2.6694 + -9.000 -0.4793 0.1959 -2.4839 + -8.000 -0.4382 0.1952 -2.2793 + -5.000 -0.2037 0.1937 -1.6869 + -4.000 -0.1174 0.1933 -1.5475 + -3.000 -0.0290 0.1930 -1.4533 + -2.000 0.0596 0.1926 -1.4732 + -1.000 0.1497 0.1923 -1.5355 + 0.000 0.2405 0.1922 -1.6025 + 1.000 0.3296 0.1922 -1.6699 + 2.000 0.4167 0.1924 -1.7374 + 3.000 0.5025 0.1927 -1.8069 + 4.000 0.5822 0.1933 -1.8707 + 6.000 0.7216 0.1948 -2.0165 + 7.000 0.7781 0.1953 -2.1120 + 8.000 0.8206 0.1961 -2.2315 + 9.000 0.8437 0.1979 -2.3414 + 11.000 0.8881 0.2035 -2.5902 + 12.000 0.9161 0.2066 -2.7957 + 13.000 0.9453 0.2101 -3.0142 + 15.000 0.9967 0.2188 -3.4850 + 16.000 1.0185 0.2240 -3.7355 + 17.000 1.0407 0.2296 -4.0092 + 18.000 1.0557 0.2362 -4.2653 + 19.000 1.0727 0.2430 -4.5442 + 20.000 1.0841 0.2508 -4.8156 + 22.000 1.0969 0.2686 -5.3459 + 25.000 1.1056 0.2973 -6.1715 + 26.000 1.1045 0.3072 -6.4219 + 30.000 1.0018 0.3622 -5.3262 + 40.000 0.8190 0.5177 -1.5368 + 50.000 0.6682 0.6842 -1.5368 + 60.000 0.5125 0.8424 -1.5368 + 70.000 0.3442 0.9739 -1.5368 + 80.000 0.1688 1.0639 -1.5368 + 90.000 0.0000 1.1024 -1.5368 + 100.000 -0.1181 1.0639 -1.5368 + 110.000 -0.2409 0.9739 -1.5368 + 120.000 -0.3588 0.8424 -1.5368 + 130.000 -0.4677 0.6842 -1.5368 + 140.000 -0.5733 0.5177 -1.5368 + 150.000 -0.7012 0.3622 -1.5368 + 160.000 -0.5948 0.2359 -1.5368 + 170.000 -0.2974 0.1952 -1.5368 + 180.000 0.0000 0.1952 -1.5368 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.1952 -1.5368 + -170.000 0.2566 0.1952 -1.5368 + -160.000 0.5133 0.2172 -1.5368 + -150.000 0.7700 0.3450 -1.5368 + -140.000 0.6151 0.5024 -1.5368 + -130.000 0.4924 0.6714 -1.5368 + -120.000 0.3720 0.8324 -1.5368 + -110.000 0.2466 0.9671 -1.5368 + -100.000 0.1195 1.0604 -1.5368 + -90.000 0.0000 1.1024 -1.5368 + -80.000 -0.1195 1.0604 -1.5368 + -70.000 -0.2466 0.9671 -1.5368 + -60.000 -0.3720 0.8324 -1.5368 + -50.000 -0.4924 0.6714 -1.5368 + -40.000 -0.6151 0.5024 -1.5368 + -30.000 -0.7700 0.3450 -1.5368 + -20.000 -0.5594 0.2714 -1.5368 + -10.000 -0.4983 0.1978 -2.6520 + -9.000 -0.5012 0.1956 -2.5277 + -8.000 -0.4434 0.1950 -2.2886 + -6.000 -0.2883 0.1939 -1.8402 + -4.000 -0.1168 0.1932 -1.5469 + -3.000 -0.0284 0.1929 -1.4542 + -2.000 0.0607 0.1926 -1.4738 + -1.000 0.1512 0.1922 -1.5364 + 0.000 0.2416 0.1921 -1.6031 + 1.000 0.3301 0.1922 -1.6704 + 2.000 0.4170 0.1924 -1.7389 + 4.000 0.5807 0.1934 -1.8673 + 5.000 0.6533 0.1941 -1.9374 + 6.000 0.7240 0.1947 -2.0211 + 7.000 0.7933 0.1951 -2.1254 + 8.000 0.8256 0.1960 -2.2370 + 9.000 0.8556 0.1975 -2.3566 + 10.000 0.8686 0.2003 -2.4430 + 11.000 0.9036 0.2026 -2.6210 + 12.000 0.9296 0.2057 -2.8243 + 13.000 0.9579 0.2093 -3.0440 + 14.000 0.9861 0.2131 -3.2803 + 16.000 1.0339 0.2226 -3.7832 + 17.000 1.0521 0.2284 -4.0463 + 18.000 1.0704 0.2346 -4.3160 + 19.000 1.0846 0.2416 -4.5892 + 20.000 1.0952 0.2494 -4.8603 + 21.000 1.1008 0.2581 -5.1154 + 24.000 1.1292 0.2837 -6.0384 + 25.000 1.1319 0.2932 -6.3250 + 26.000 1.1322 0.3029 -6.5941 + 27.000 1.1293 0.3128 -6.8379 + 28.000 1.1221 0.3232 -7.0450 + 29.000 1.1118 0.3340 -7.2160 + 30.000 1.1000 0.3450 -7.3593 + 40.000 0.8788 0.5024 -1.5368 + 50.000 0.7034 0.6714 -1.5368 + 60.000 0.5315 0.8324 -1.5368 + 70.000 0.3523 0.9671 -1.5368 + 80.000 0.1708 1.0604 -1.5368 + 90.000 0.0000 1.1024 -1.5368 + 100.000 -0.1195 1.0604 -1.5368 + 110.000 -0.2466 0.9671 -1.5368 + 120.000 -0.3720 0.8324 -1.5368 + 130.000 -0.4924 0.6714 -1.5368 + 140.000 -0.6151 0.5024 -1.5368 + 150.000 -0.7700 0.3450 -1.5368 + 160.000 -0.5133 0.2172 -1.5368 + 170.000 -0.2566 0.1952 -1.5368 + 180.000 0.0000 0.1952 -1.5368 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.1952 -1.5368 + -170.000 0.2703 0.1952 -1.5368 + -160.000 0.5406 0.2196 -1.5368 + -150.000 0.7643 0.3471 -1.5368 + -140.000 0.6117 0.5044 -1.5368 + -130.000 0.4904 0.6730 -1.5368 + -120.000 0.3709 0.8337 -1.5368 + -110.000 0.2462 0.9680 -1.5368 + -100.000 0.1194 1.0609 -1.5368 + -90.000 0.0000 1.1024 -1.5368 + -80.000 -0.1194 1.0609 -1.5368 + -70.000 -0.2462 0.9680 -1.5368 + -60.000 -0.3709 0.8337 -1.5368 + -50.000 -0.4904 0.6730 -1.5368 + -40.000 -0.6117 0.5044 -1.5368 + -30.000 -0.7643 0.3471 -1.5368 + -20.000 -0.5810 0.2686 -1.5368 + -10.000 -0.5080 0.1973 -2.6736 + -7.000 -0.3695 0.1943 -2.0409 + -6.000 -0.2876 0.1939 -1.8319 + -5.000 -0.2035 0.1934 -1.6869 + -4.000 -0.1167 0.1931 -1.5466 + -3.000 -0.0277 0.1929 -1.4563 + -2.000 0.0619 0.1926 -1.4744 + -1.000 0.1520 0.1921 -1.5370 + 0.000 0.2422 0.1921 -1.6033 + 1.000 0.3306 0.1921 -1.6709 + 2.000 0.4176 0.1924 -1.7360 + 3.000 0.5021 0.1927 -1.7997 + 4.000 0.5811 0.1933 -1.8700 + 5.000 0.6538 0.1940 -1.9394 + 6.000 0.7290 0.1945 -2.0259 + 7.000 0.7988 0.1950 -2.1309 + 8.000 0.8306 0.1959 -2.2430 + 10.000 0.8799 0.1997 -2.4620 + 11.000 0.9129 0.2021 -2.6398 + 12.000 0.9445 0.2049 -2.8562 + 13.000 0.9744 0.2081 -3.0830 + 14.000 0.9963 0.2124 -3.3057 + 15.000 1.0211 0.2168 -3.5530 + 17.000 1.0629 0.2274 -4.0818 + 18.000 1.0801 0.2336 -4.3493 + 19.000 1.0941 0.2406 -4.6256 + 20.000 1.1012 0.2487 -4.8838 + 22.000 1.1309 0.2638 -5.5040 + 23.000 1.1367 0.2728 -5.8037 + 24.000 1.1409 0.2820 -6.1025 + 25.000 1.1429 0.2916 -6.3882 + 26.000 1.1421 0.3014 -6.6553 + 27.000 1.1368 0.3116 -6.8875 + 28.000 1.1290 0.3221 -7.0932 + 29.000 1.1198 0.3327 -7.2756 + 30.000 1.0919 0.3471 -6.9240 + 40.000 0.8738 0.5044 -1.5368 + 50.000 0.7005 0.6730 -1.5368 + 60.000 0.5299 0.8337 -1.5368 + 70.000 0.3517 0.9680 -1.5368 + 80.000 0.1706 1.0609 -1.5368 + 90.000 0.0000 1.1024 -1.5368 + 100.000 -0.1194 1.0609 -1.5368 + 110.000 -0.2462 0.9680 -1.5368 + 120.000 -0.3709 0.8337 -1.5368 + 130.000 -0.4904 0.6730 -1.5368 + 140.000 -0.6117 0.5044 -1.5368 + 150.000 -0.7643 0.3471 -1.5368 + 160.000 -0.5406 0.2196 -1.5368 + 170.000 -0.2703 0.1952 -1.5368 + 180.000 0.0000 0.1952 -1.5368 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.1952 -1.5368 + -170.000 0.2605 0.1952 -1.5368 + -160.000 0.5210 0.2143 -1.5368 + -150.000 0.7815 0.3423 -1.5368 + -140.000 0.6221 0.5001 -1.5368 + -130.000 0.4965 0.6694 -1.5368 + -120.000 0.3742 0.8309 -1.5368 + -110.000 0.2476 0.9661 -1.5368 + -100.000 0.1198 1.0599 -1.5368 + -90.000 0.0000 1.1024 -1.5368 + -80.000 -0.1198 1.0599 -1.5368 + -70.000 -0.2476 0.9661 -1.5368 + -60.000 -0.3742 0.8309 -1.5368 + -50.000 -0.4965 0.6694 -1.5368 + -40.000 -0.6221 0.5001 -1.5368 + -30.000 -0.7815 0.3423 -1.5368 + -20.000 -0.5719 0.2696 -1.5368 + -10.000 -0.5178 0.1970 -2.6942 + -9.000 -0.5035 0.1956 -2.5224 + -8.000 -0.4482 0.1946 -2.2979 + -6.000 -0.2875 0.1938 -1.8301 + -5.000 -0.2034 0.1933 -1.6867 + -4.000 -0.1166 0.1929 -1.5465 + -3.000 -0.0271 0.1928 -1.4566 + -2.000 0.0627 0.1925 -1.4749 + -1.000 0.1524 0.1921 -1.5371 + 0.000 0.2429 0.1921 -1.6039 + 1.000 0.3298 0.1922 -1.6711 + 2.000 0.4175 0.1924 -1.7354 + 3.000 0.5011 0.1928 -1.7984 + 5.000 0.6561 0.1940 -1.9418 + 6.000 0.7312 0.1945 -2.0284 + 7.000 0.8043 0.1948 -2.1363 + 8.000 0.8337 0.1957 -2.2463 + 11.000 0.9214 0.2016 -2.6567 + 12.000 0.9530 0.2044 -2.8740 + 14.000 1.0117 0.2112 -3.3444 + 16.000 1.0521 0.2210 -3.8395 + 18.000 1.0883 0.2327 -4.3774 + 21.000 1.1323 0.2540 -5.2529 + 22.000 1.1397 0.2626 -5.5436 + 23.000 1.1462 0.2715 -5.8524 + 24.000 1.1497 0.2808 -6.1500 + 25.000 1.1508 0.2905 -6.4340 + 26.000 1.1476 0.3006 -6.6888 + 27.000 1.1424 0.3108 -6.9235 + 28.000 1.1355 0.3211 -7.1382 + 29.000 1.1271 0.3316 -7.3297 + 30.000 1.1164 0.3423 -7.4909 + 40.000 0.8887 0.5001 -1.5368 + 50.000 0.7093 0.6694 -1.5368 + 60.000 0.5346 0.8309 -1.5368 + 70.000 0.3537 0.9661 -1.5368 + 80.000 0.1711 1.0599 -1.5368 + 90.000 0.0000 1.1024 -1.5368 + 100.000 -0.1198 1.0599 -1.5368 + 110.000 -0.2476 0.9661 -1.5368 + 120.000 -0.3742 0.8309 -1.5368 + 130.000 -0.4965 0.6694 -1.5368 + 140.000 -0.6221 0.5001 -1.5368 + 150.000 -0.7815 0.3423 -1.5368 + 160.000 -0.5210 0.2143 -1.5368 + 170.000 -0.2605 0.1952 -1.5368 + 180.000 0.0000 0.1952 -1.5368 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0444_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0444_coords.txt new file mode 100644 index 00000000..690c1efd --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0444_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0444 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.038173 + 0.027091 0.077420 + 0.060263 0.116187 + 0.105430 0.151821 + 0.161359 0.183011 + 0.226526 0.208215 + 0.299152 0.226025 + 0.377257 0.234704 + 0.458710 0.233617 + 0.541290 0.223836 + 0.622743 0.206871 + 0.700848 0.184493 + 0.773474 0.158713 + 0.838641 0.131307 + 0.894570 0.103562 + 0.939737 0.076248 + 0.972909 0.049770 + 0.993181 0.024310 + 1.000000 0.000000 + 0.993181 -0.022489 + 0.972909 -0.044262 + 0.939737 -0.066198 + 0.894570 -0.088734 + 0.838641 -0.111957 + 0.773474 -0.135477 + 0.700848 -0.158393 + 0.622743 -0.179140 + 0.541290 -0.195779 + 0.458710 -0.206420 + 0.377257 -0.209286 + 0.299152 -0.203115 + 0.226526 -0.188588 + 0.161359 -0.167145 + 0.105430 -0.140070 + 0.060263 -0.108468 + 0.027091 -0.073433 + 0.006819 -0.036544 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0629.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0629.dat new file mode 100644 index 00000000..c6856a16 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0629.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0629 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0629_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.1584 -2.0237 + -170.000 0.1523 0.1584 -2.0237 + -160.000 0.3046 0.1880 -2.0237 + -150.000 0.4569 0.2721 -2.0237 + -140.000 0.3758 0.3756 -2.0237 + -130.000 0.3081 0.4864 -2.0237 + -120.000 0.2373 0.5916 -2.0237 + -110.000 0.1599 0.6790 -2.0237 + -100.000 0.0786 0.7385 -2.0237 + -90.000 0.0000 0.7637 -2.0237 + -80.000 -0.0786 0.7385 -2.0237 + -70.000 -0.1599 0.6790 -2.0237 + -60.000 -0.2373 0.5916 -2.0237 + -50.000 -0.3081 0.4864 -2.0237 + -40.000 -0.3758 0.3756 -2.0237 + -30.000 -0.4569 0.2721 -2.0237 + -20.000 -0.3311 0.2173 -2.0237 + -10.000 -0.2932 0.1625 -2.6904 + -9.000 -0.2784 0.1609 -2.5779 + -8.000 -0.2637 0.1596 -2.4693 + -7.000 -0.2374 0.1590 -2.3441 + -6.000 -0.1909 0.1585 -2.2226 + -5.000 -0.1381 0.1581 -2.1261 + -4.000 -0.0829 0.1578 -2.0357 + -3.000 -0.0267 0.1573 -1.9776 + -2.000 0.0328 0.1572 -1.9772 + -1.000 0.0920 0.1571 -2.0182 + 0.000 0.1509 0.1572 -2.0616 + 1.000 0.2102 0.1572 -2.1064 + 2.000 0.2686 0.1573 -2.1510 + 3.000 0.3259 0.1574 -2.1973 + 4.000 0.3811 0.1576 -2.2439 + 5.000 0.4355 0.1578 -2.2951 + 6.000 0.4799 0.1583 -2.3482 + 7.000 0.4977 0.1591 -2.3882 + 8.000 0.5139 0.1602 -2.4500 + 9.000 0.5337 0.1617 -2.5244 + 10.000 0.5542 0.1633 -2.6021 + 11.000 0.5581 0.1662 -2.6596 + 12.000 0.5726 0.1688 -2.7821 + 13.000 0.5773 0.1727 -2.8865 + 14.000 0.5900 0.1762 -3.0158 + 15.000 0.5991 0.1804 -3.1420 + 16.000 0.6130 0.1845 -3.2909 + 17.000 0.6251 0.1889 -3.4442 + 18.000 0.6364 0.1938 -3.6062 + 19.000 0.6469 0.1990 -3.7685 + 20.000 0.6560 0.2045 -3.9359 + 21.000 0.6645 0.2101 -4.1074 + 22.000 0.6741 0.2156 -4.2915 + 23.000 0.6782 0.2219 -4.4584 + 24.000 0.6815 0.2283 -4.6230 + 25.000 0.6820 0.2350 -4.7783 + 26.000 0.6796 0.2421 -4.9112 + 28.000 0.6675 0.2567 -5.1044 + 29.000 0.6584 0.2648 -5.1534 + 30.000 0.6527 0.2721 -5.2137 + 40.000 0.5369 0.3756 -2.0237 + 50.000 0.4402 0.4864 -2.0237 + 60.000 0.3390 0.5916 -2.0237 + 70.000 0.2284 0.6790 -2.0237 + 80.000 0.1123 0.7385 -2.0237 + 90.000 0.0000 0.7637 -2.0237 + 100.000 -0.0786 0.7385 -2.0237 + 110.000 -0.1599 0.6790 -2.0237 + 120.000 -0.2373 0.5916 -2.0237 + 130.000 -0.3081 0.4864 -2.0237 + 140.000 -0.3758 0.3756 -2.0237 + 150.000 -0.4569 0.2721 -2.0237 + 160.000 -0.3046 0.1880 -2.0237 + 170.000 -0.1523 0.1584 -2.0237 + 180.000 0.0000 0.1584 -2.0237 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.3478 -2.0237 + -170.000 0.1596 0.3478 -2.0237 + -160.000 0.3193 0.3716 -2.0237 + -150.000 0.4789 0.4561 -2.0237 + -140.000 0.3893 0.5602 -2.0237 + -130.000 0.3160 0.6718 -2.0237 + -120.000 0.2415 0.7778 -2.0237 + -110.000 0.1617 0.8662 -2.0237 + -100.000 0.0790 0.9268 -2.0237 + -90.000 0.0000 0.9531 -2.0237 + -80.000 -0.0790 0.9268 -2.0237 + -70.000 -0.1617 0.8662 -2.0237 + -60.000 -0.2415 0.7778 -2.0237 + -50.000 -0.3160 0.6718 -2.0237 + -40.000 -0.3893 0.5602 -2.0237 + -30.000 -0.4789 0.4561 -2.0237 + -20.000 -0.3500 0.4033 -2.0237 + -10.000 -0.3157 0.3505 -2.7378 + -9.000 -0.2927 0.3494 -2.6052 + -8.000 -0.2832 0.3484 -2.5029 + -7.000 -0.2416 0.3478 -2.3517 + -6.000 -0.1909 0.3474 -2.2228 + -5.000 -0.1372 0.3471 -2.1252 + -4.000 -0.0800 0.3468 -2.0327 + -3.000 -0.0222 0.3465 -1.9744 + -1.000 0.0968 0.3461 -2.0210 + 0.000 0.1568 0.3461 -2.0653 + 1.000 0.2159 0.3462 -2.1100 + 2.000 0.2756 0.3462 -2.1555 + 5.000 0.4382 0.3470 -2.2965 + 6.000 0.4769 0.3477 -2.3466 + 7.000 0.5033 0.3483 -2.3927 + 9.000 0.5529 0.3501 -2.5482 + 10.000 0.5627 0.3521 -2.6131 + 11.000 0.5796 0.3542 -2.7011 + 12.000 0.5872 0.3571 -2.8127 + 13.000 0.6011 0.3601 -2.9399 + 14.000 0.6151 0.3633 -3.0792 + 15.000 0.6317 0.3666 -3.2303 + 16.000 0.6451 0.3705 -3.3866 + 17.000 0.6589 0.3745 -3.5565 + 18.000 0.6704 0.3791 -3.7258 + 19.000 0.6818 0.3838 -3.8997 + 20.000 0.6890 0.3894 -4.0719 + 21.000 0.6966 0.3950 -4.2477 + 22.000 0.7031 0.4009 -4.4304 + 23.000 0.7053 0.4073 -4.5965 + 24.000 0.7121 0.4131 -4.7982 + 25.000 0.7124 0.4197 -4.9655 + 26.000 0.7128 0.4262 -5.1291 + 27.000 0.7109 0.4330 -5.2741 + 28.000 0.7070 0.4400 -5.3976 + 29.000 0.6923 0.4485 -5.4307 + 30.000 0.6842 0.4561 -5.4947 + 40.000 0.5561 0.5602 -2.0237 + 50.000 0.4515 0.6718 -2.0237 + 60.000 0.3450 0.7778 -2.0237 + 70.000 0.2309 0.8662 -2.0237 + 80.000 0.1129 0.9268 -2.0237 + 90.000 0.0000 0.9531 -2.0237 + 100.000 -0.0790 0.9268 -2.0237 + 110.000 -0.1617 0.8662 -2.0237 + 120.000 -0.2415 0.7778 -2.0237 + 130.000 -0.3160 0.6718 -2.0237 + 140.000 -0.3893 0.5602 -2.0237 + 150.000 -0.4789 0.4561 -2.0237 + 160.000 -0.3193 0.3716 -2.0237 + 170.000 -0.1596 0.3478 -2.0237 + 180.000 0.0000 0.3478 -2.0237 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.3632 -2.0237 + -170.000 0.1656 0.3632 -2.0237 + -160.000 0.3312 0.3825 -2.0237 + -150.000 0.4967 0.4674 -2.0237 + -140.000 0.4001 0.5720 -2.0237 + -130.000 0.3224 0.6841 -2.0237 + -120.000 0.2450 0.7908 -2.0237 + -110.000 0.1631 0.8799 -2.0237 + -100.000 0.0794 0.9414 -2.0237 + -90.000 0.0000 0.9685 -2.0237 + -80.000 -0.0794 0.9414 -2.0237 + -70.000 -0.1631 0.8799 -2.0237 + -60.000 -0.2450 0.7908 -2.0237 + -50.000 -0.3224 0.6841 -2.0237 + -40.000 -0.4001 0.5720 -2.0237 + -30.000 -0.4967 0.4674 -2.0237 + -20.000 -0.3634 0.4163 -2.0237 + -10.000 -0.3287 0.3652 -2.7651 + -9.000 -0.3081 0.3641 -2.6335 + -8.000 -0.2884 0.3634 -2.5120 + -7.000 -0.2425 0.3630 -2.3531 + -6.000 -0.1917 0.3626 -2.2240 + -5.000 -0.1361 0.3622 -2.1241 + -4.000 -0.0786 0.3620 -2.0311 + -3.000 -0.0205 0.3618 -1.9734 + -2.000 0.0387 0.3614 -1.9806 + -1.000 0.0989 0.3613 -2.0223 + 0.000 0.1588 0.3613 -2.0664 + 1.000 0.2192 0.3613 -2.1121 + 2.000 0.2774 0.3614 -2.1568 + 4.000 0.3889 0.3619 -2.2512 + 5.000 0.4367 0.3624 -2.2964 + 6.000 0.4784 0.3630 -2.3443 + 7.000 0.5099 0.3634 -2.3993 + 8.000 0.5401 0.3640 -2.4785 + 9.000 0.5570 0.3652 -2.5530 + 10.000 0.5749 0.3668 -2.6297 + 11.000 0.5865 0.3690 -2.7146 + 12.000 0.6012 0.3715 -2.8423 + 13.000 0.6143 0.3743 -2.9702 + 14.000 0.6330 0.3772 -3.1241 + 15.000 0.6477 0.3805 -3.2751 + 16.000 0.6622 0.3841 -3.4373 + 17.000 0.6755 0.3881 -3.6111 + 19.000 0.6970 0.3973 -3.9581 + 20.000 0.7131 0.4015 -4.1697 + 21.000 0.7191 0.4072 -4.3441 + 22.000 0.7228 0.4134 -4.5231 + 23.000 0.7251 0.4197 -4.6981 + 24.000 0.7282 0.4260 -4.8884 + 25.000 0.7295 0.4325 -5.0675 + 26.000 0.7282 0.4392 -5.2283 + 27.000 0.7248 0.4462 -5.3695 + 28.000 0.7208 0.4531 -5.4989 + 29.000 0.7159 0.4602 -5.6135 + 30.000 0.7096 0.4674 -5.7066 + 40.000 0.5715 0.5720 -2.0237 + 50.000 0.4606 0.6841 -2.0237 + 60.000 0.3500 0.7908 -2.0237 + 70.000 0.2331 0.8799 -2.0237 + 80.000 0.1134 0.9414 -2.0237 + 90.000 0.0000 0.9685 -2.0237 + 100.000 -0.0794 0.9414 -2.0237 + 110.000 -0.1631 0.8799 -2.0237 + 120.000 -0.2450 0.7908 -2.0237 + 130.000 -0.3224 0.6841 -2.0237 + 140.000 -0.4001 0.5720 -2.0237 + 150.000 -0.4967 0.4674 -2.0237 + 160.000 -0.3312 0.3825 -2.0237 + 170.000 -0.1656 0.3632 -2.0237 + 180.000 0.0000 0.3632 -2.0237 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.3632 -2.0237 + -170.000 0.1984 0.3632 -2.0237 + -160.000 0.3969 0.3903 -2.0237 + -150.000 0.4679 0.4746 -2.0237 + -140.000 0.3825 0.5784 -2.0237 + -130.000 0.3121 0.6895 -2.0237 + -120.000 0.2394 0.7950 -2.0237 + -110.000 0.1608 0.8828 -2.0237 + -100.000 0.0788 0.9428 -2.0237 + -90.000 0.0000 0.9685 -2.0237 + -80.000 -0.0788 0.9428 -2.0237 + -70.000 -0.1608 0.8828 -2.0237 + -60.000 -0.2394 0.7950 -2.0237 + -50.000 -0.3121 0.6895 -2.0237 + -40.000 -0.3825 0.5784 -2.0237 + -30.000 -0.4679 0.4746 -2.0237 + -20.000 -0.4101 0.4105 -2.0237 + -10.000 -0.3337 0.3649 -2.7794 + -9.000 -0.3198 0.3637 -2.6556 + -8.000 -0.2924 0.3632 -2.5191 + -5.000 -0.1360 0.3621 -2.1238 + -4.000 -0.0783 0.3619 -2.0308 + -3.000 -0.0193 0.3617 -1.9679 + -2.000 0.0398 0.3614 -1.9812 + -1.000 0.0999 0.3612 -2.0228 + 0.000 0.1605 0.3612 -2.0675 + 1.000 0.2199 0.3612 -2.1125 + 2.000 0.2781 0.3613 -2.1575 + 3.000 0.3353 0.3615 -2.2039 + 4.000 0.3885 0.3619 -2.2464 + 6.000 0.4815 0.3629 -2.3438 + 7.000 0.5192 0.3632 -2.4075 + 8.000 0.5476 0.3638 -2.4872 + 9.000 0.5629 0.3650 -2.5606 + 11.000 0.5926 0.3687 -2.7266 + 12.000 0.6113 0.3708 -2.8637 + 13.000 0.6308 0.3731 -3.0095 + 15.000 0.6651 0.3789 -3.3236 + 16.000 0.6796 0.3824 -3.4907 + 17.000 0.6944 0.3861 -3.6734 + 18.000 0.7045 0.3905 -3.8443 + 19.000 0.7158 0.3950 -4.0304 + 20.000 0.7234 0.4003 -4.2115 + 22.000 0.7319 0.4121 -4.5653 + 25.000 0.7378 0.4313 -5.1162 + 26.000 0.7370 0.4379 -5.2833 + 30.000 0.6684 0.4746 -4.5522 + 40.000 0.5465 0.5784 -2.0237 + 50.000 0.4458 0.6895 -2.0237 + 60.000 0.3420 0.7950 -2.0237 + 70.000 0.2297 0.8828 -2.0237 + 80.000 0.1126 0.9428 -2.0237 + 90.000 0.0000 0.9685 -2.0237 + 100.000 -0.0788 0.9428 -2.0237 + 110.000 -0.1608 0.8828 -2.0237 + 120.000 -0.2394 0.7950 -2.0237 + 130.000 -0.3121 0.6895 -2.0237 + 140.000 -0.3825 0.5784 -2.0237 + 150.000 -0.4679 0.4746 -2.0237 + 160.000 -0.3969 0.3903 -2.0237 + 170.000 -0.1984 0.3632 -2.0237 + 180.000 0.0000 0.3632 -2.0237 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.3632 -2.0237 + -170.000 0.1712 0.3632 -2.0237 + -160.000 0.3425 0.3778 -2.0237 + -150.000 0.5138 0.4631 -2.0237 + -140.000 0.4104 0.5681 -2.0237 + -130.000 0.3286 0.6809 -2.0237 + -120.000 0.2482 0.7884 -2.0237 + -110.000 0.1646 0.8782 -2.0237 + -100.000 0.0798 0.9405 -2.0237 + -90.000 0.0000 0.9685 -2.0237 + -80.000 -0.0798 0.9405 -2.0237 + -70.000 -0.1646 0.8782 -2.0237 + -60.000 -0.2482 0.7884 -2.0237 + -50.000 -0.3286 0.6809 -2.0237 + -40.000 -0.4104 0.5681 -2.0237 + -30.000 -0.5138 0.4631 -2.0237 + -20.000 -0.3732 0.4140 -2.0237 + -10.000 -0.3325 0.3649 -2.7678 + -9.000 -0.3344 0.3635 -2.6848 + -8.000 -0.2959 0.3630 -2.5253 + -6.000 -0.1924 0.3623 -2.2261 + -4.000 -0.0779 0.3618 -2.0304 + -3.000 -0.0189 0.3617 -1.9686 + -2.000 0.0405 0.3614 -1.9816 + -1.000 0.1009 0.3612 -2.0234 + 0.000 0.1612 0.3611 -2.0679 + 1.000 0.2203 0.3612 -2.1128 + 2.000 0.2782 0.3613 -2.1585 + 4.000 0.3875 0.3620 -2.2442 + 5.000 0.4359 0.3624 -2.2910 + 6.000 0.4831 0.3628 -2.3468 + 7.000 0.5293 0.3631 -2.4164 + 8.000 0.5509 0.3637 -2.4909 + 9.000 0.5709 0.3647 -2.5707 + 10.000 0.5796 0.3665 -2.6284 + 11.000 0.6029 0.3681 -2.7471 + 12.000 0.6203 0.3702 -2.8827 + 13.000 0.6392 0.3725 -3.0293 + 14.000 0.6580 0.3751 -3.1870 + 16.000 0.6899 0.3815 -3.5226 + 17.000 0.7020 0.3853 -3.6982 + 18.000 0.7142 0.3895 -3.8781 + 19.000 0.7237 0.3941 -4.0604 + 20.000 0.7308 0.3993 -4.2413 + 21.000 0.7345 0.4052 -4.4116 + 24.000 0.7535 0.4222 -5.0274 + 25.000 0.7553 0.4285 -5.2186 + 26.000 0.7555 0.4350 -5.3982 + 27.000 0.7535 0.4416 -5.5609 + 28.000 0.7487 0.4485 -5.6991 + 29.000 0.7419 0.4558 -5.8132 + 30.000 0.7340 0.4631 -5.9088 + 40.000 0.5864 0.5681 -2.0237 + 50.000 0.4694 0.6809 -2.0237 + 60.000 0.3546 0.7884 -2.0237 + 70.000 0.2351 0.8782 -2.0237 + 80.000 0.1139 0.9405 -2.0237 + 90.000 0.0000 0.9685 -2.0237 + 100.000 -0.0798 0.9405 -2.0237 + 110.000 -0.1646 0.8782 -2.0237 + 120.000 -0.2482 0.7884 -2.0237 + 130.000 -0.3286 0.6809 -2.0237 + 140.000 -0.4104 0.5681 -2.0237 + 150.000 -0.5138 0.4631 -2.0237 + 160.000 -0.3425 0.3778 -2.0237 + 170.000 -0.1712 0.3632 -2.0237 + 180.000 0.0000 0.3632 -2.0237 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.3632 -2.0237 + -170.000 0.1804 0.3632 -2.0237 + -160.000 0.3607 0.3794 -2.0237 + -150.000 0.5100 0.4645 -2.0237 + -140.000 0.4081 0.5695 -2.0237 + -130.000 0.3272 0.6820 -2.0237 + -120.000 0.2475 0.7892 -2.0237 + -110.000 0.1643 0.8788 -2.0237 + -100.000 0.0797 0.9408 -2.0237 + -90.000 0.0000 0.9685 -2.0237 + -80.000 -0.0797 0.9408 -2.0237 + -70.000 -0.1643 0.8788 -2.0237 + -60.000 -0.2475 0.7892 -2.0237 + -50.000 -0.3272 0.6820 -2.0237 + -40.000 -0.4081 0.5695 -2.0237 + -30.000 -0.5100 0.4645 -2.0237 + -20.000 -0.3877 0.4121 -2.0237 + -10.000 -0.3390 0.3646 -2.7822 + -7.000 -0.2466 0.3626 -2.3600 + -6.000 -0.1919 0.3623 -2.2206 + -5.000 -0.1358 0.3620 -2.1238 + -4.000 -0.0779 0.3618 -2.0302 + -3.000 -0.0185 0.3616 -1.9699 + -2.000 0.0413 0.3614 -1.9820 + -1.000 0.1014 0.3611 -2.0238 + 0.000 0.1616 0.3611 -2.0680 + 1.000 0.2206 0.3611 -2.1132 + 2.000 0.2786 0.3613 -2.1566 + 3.000 0.3350 0.3615 -2.1991 + 4.000 0.3877 0.3619 -2.2460 + 5.000 0.4363 0.3624 -2.2923 + 6.000 0.4864 0.3627 -2.3500 + 7.000 0.5330 0.3630 -2.4201 + 8.000 0.5543 0.3636 -2.4949 + 10.000 0.5871 0.3661 -2.6410 + 11.000 0.6091 0.3678 -2.7596 + 12.000 0.6303 0.3696 -2.9040 + 13.000 0.6502 0.3718 -3.0554 + 14.000 0.6648 0.3746 -3.2040 + 15.000 0.6814 0.3776 -3.3690 + 17.000 0.7092 0.3846 -3.7218 + 18.000 0.7207 0.3888 -3.9004 + 19.000 0.7301 0.3934 -4.0847 + 20.000 0.7348 0.3989 -4.2570 + 22.000 0.7546 0.4089 -4.6708 + 23.000 0.7585 0.4150 -4.8708 + 24.000 0.7613 0.4211 -5.0702 + 25.000 0.7626 0.4275 -5.2609 + 26.000 0.7621 0.4341 -5.4390 + 27.000 0.7585 0.4408 -5.5940 + 28.000 0.7534 0.4479 -5.7312 + 29.000 0.7472 0.4549 -5.8529 + 30.000 0.7286 0.4645 -5.6184 + 40.000 0.5831 0.5695 -2.0237 + 50.000 0.4674 0.6820 -2.0237 + 60.000 0.3536 0.7892 -2.0237 + 70.000 0.2347 0.8788 -2.0237 + 80.000 0.1138 0.9408 -2.0237 + 90.000 0.0000 0.9685 -2.0237 + 100.000 -0.0797 0.9408 -2.0237 + 110.000 -0.1643 0.8788 -2.0237 + 120.000 -0.2475 0.7892 -2.0237 + 130.000 -0.3272 0.6820 -2.0237 + 140.000 -0.4081 0.5695 -2.0237 + 150.000 -0.5100 0.4645 -2.0237 + 160.000 -0.3607 0.3794 -2.0237 + 170.000 -0.1804 0.3632 -2.0237 + 180.000 0.0000 0.3632 -2.0237 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.3632 -2.0237 + -170.000 0.1738 0.3632 -2.0237 + -160.000 0.3476 0.3759 -2.0237 + -150.000 0.5215 0.4613 -2.0237 + -140.000 0.4151 0.5666 -2.0237 + -130.000 0.3313 0.6796 -2.0237 + -120.000 0.2497 0.7873 -2.0237 + -110.000 0.1652 0.8775 -2.0237 + -100.000 0.0799 0.9401 -2.0237 + -90.000 0.0000 0.9685 -2.0237 + -80.000 -0.0799 0.9401 -2.0237 + -70.000 -0.1652 0.8775 -2.0237 + -60.000 -0.2497 0.7873 -2.0237 + -50.000 -0.3313 0.6796 -2.0237 + -40.000 -0.4151 0.5666 -2.0237 + -30.000 -0.5215 0.4613 -2.0237 + -20.000 -0.3816 0.4128 -2.0237 + -10.000 -0.3455 0.3643 -2.7960 + -9.000 -0.3360 0.3634 -2.6813 + -8.000 -0.2991 0.3628 -2.5315 + -6.000 -0.1918 0.3622 -2.2194 + -5.000 -0.1357 0.3619 -2.1237 + -4.000 -0.0778 0.3617 -2.0301 + -3.000 -0.0181 0.3616 -1.9701 + -2.000 0.0418 0.3614 -1.9823 + -1.000 0.1017 0.3611 -2.0239 + 0.000 0.1621 0.3611 -2.0684 + 1.000 0.2201 0.3612 -2.1133 + 2.000 0.2786 0.3613 -2.1562 + 3.000 0.3343 0.3616 -2.1982 + 5.000 0.4378 0.3623 -2.2939 + 6.000 0.4879 0.3627 -2.3517 + 7.000 0.5367 0.3629 -2.4237 + 8.000 0.5563 0.3635 -2.4971 + 11.000 0.6148 0.3675 -2.7710 + 12.000 0.6359 0.3693 -2.9159 + 14.000 0.6751 0.3738 -3.2298 + 16.000 0.7020 0.3804 -3.5602 + 18.000 0.7262 0.3882 -3.9191 + 21.000 0.7555 0.4024 -4.5033 + 22.000 0.7605 0.4081 -4.6972 + 23.000 0.7648 0.4141 -4.9033 + 24.000 0.7671 0.4203 -5.1019 + 25.000 0.7679 0.4267 -5.2914 + 26.000 0.7657 0.4335 -5.4614 + 27.000 0.7623 0.4403 -5.6180 + 28.000 0.7577 0.4472 -5.7613 + 29.000 0.7521 0.4542 -5.8891 + 30.000 0.7449 0.4613 -5.9967 + 40.000 0.5930 0.5666 -2.0237 + 50.000 0.4733 0.6796 -2.0237 + 60.000 0.3567 0.7873 -2.0237 + 70.000 0.2360 0.8775 -2.0237 + 80.000 0.1142 0.9401 -2.0237 + 90.000 0.0000 0.9685 -2.0237 + 100.000 -0.0799 0.9401 -2.0237 + 110.000 -0.1652 0.8775 -2.0237 + 120.000 -0.2497 0.7873 -2.0237 + 130.000 -0.3313 0.6796 -2.0237 + 140.000 -0.4151 0.5666 -2.0237 + 150.000 -0.5215 0.4613 -2.0237 + 160.000 -0.3476 0.3759 -2.0237 + 170.000 -0.1738 0.3632 -2.0237 + 180.000 0.0000 0.3632 -2.0237 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0629_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0629_coords.txt new file mode 100644 index 00000000..0384c9cb --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0629_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0629 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.053204 + 0.027091 0.106260 + 0.060263 0.157538 + 0.105430 0.204545 + 0.161359 0.245774 + 0.226526 0.279641 + 0.299152 0.304748 + 0.377257 0.319589 + 0.458710 0.323479 + 0.541290 0.317019 + 0.622743 0.301206 + 0.700848 0.277317 + 0.773474 0.246947 + 0.838641 0.211626 + 0.894570 0.172671 + 0.939737 0.131160 + 0.972909 0.087998 + 0.993181 0.044048 + 1.000000 0.000000 + 0.993181 -0.042845 + 0.972909 -0.084360 + 0.939737 -0.124522 + 0.894570 -0.162878 + 0.838641 -0.198845 + 0.773474 -0.231600 + 0.700848 -0.260079 + 0.622743 -0.282891 + 0.541290 -0.298488 + 0.458710 -0.305516 + 0.377257 -0.302801 + 0.299152 -0.289617 + 0.226526 -0.266678 + 0.161359 -0.235296 + 0.105430 -0.196784 + 0.060263 -0.152440 + 0.027091 -0.103626 + 0.006819 -0.052128 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0864.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_0864.dat new file mode 100644 index 00000000..d9dc199d --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0864.dat @@ -0,0 +1,560 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_0864 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_0864_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 72 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.2481 -2.6421 + -170.000 0.0558 0.2481 -2.6421 + -160.000 0.1117 0.2589 -2.6421 + -150.000 0.1675 0.2898 -2.6421 + -140.000 0.1378 0.3277 -2.6421 + -130.000 0.1130 0.3683 -2.6421 + -120.000 0.0870 0.4069 -2.6421 + -110.000 0.0586 0.4389 -2.6421 + -100.000 0.0288 0.4607 -2.6421 + -90.000 0.0000 0.4700 -2.6421 + -80.000 -0.0288 0.4607 -2.6421 + -70.000 -0.0586 0.4389 -2.6421 + -60.000 -0.0870 0.4069 -2.6421 + -50.000 -0.1130 0.3683 -2.6421 + -40.000 -0.1378 0.3277 -2.6421 + -30.000 -0.1675 0.2898 -2.6421 + -20.000 -0.1214 0.2697 -2.6421 + -10.000 -0.1075 0.2496 -2.8865 + -9.000 -0.1021 0.2490 -2.8453 + -8.000 -0.0966 0.2485 -2.8054 + -7.000 -0.0870 0.2483 -2.7596 + -6.000 -0.0700 0.2481 -2.7150 + -5.000 -0.0506 0.2480 -2.6796 + -4.000 -0.0304 0.2479 -2.6465 + -3.000 -0.0098 0.2477 -2.6252 + -2.000 0.0120 0.2476 -2.6251 + -1.000 0.0337 0.2476 -2.6401 + 0.000 0.0553 0.2476 -2.6560 + 1.000 0.0771 0.2476 -2.6724 + 2.000 0.0985 0.2477 -2.6888 + 3.000 0.1195 0.2477 -2.7058 + 4.000 0.1397 0.2478 -2.7228 + 5.000 0.1596 0.2479 -2.7416 + 6.000 0.1759 0.2481 -2.7611 + 7.000 0.1825 0.2484 -2.7757 + 8.000 0.1884 0.2488 -2.7984 + 9.000 0.1956 0.2493 -2.8257 + 10.000 0.2031 0.2499 -2.8541 + 11.000 0.2046 0.2510 -2.8752 + 12.000 0.2099 0.2519 -2.9201 + 13.000 0.2116 0.2533 -2.9584 + 14.000 0.2163 0.2546 -3.0058 + 15.000 0.2196 0.2562 -3.0520 + 16.000 0.2247 0.2577 -3.1066 + 17.000 0.2292 0.2593 -3.1628 + 18.000 0.2333 0.2611 -3.2222 + 19.000 0.2371 0.2630 -3.2817 + 20.000 0.2405 0.2650 -3.3431 + 21.000 0.2436 0.2671 -3.4059 + 22.000 0.2471 0.2691 -3.4734 + 23.000 0.2486 0.2714 -3.5346 + 24.000 0.2498 0.2737 -3.5950 + 25.000 0.2500 0.2762 -3.6519 + 26.000 0.2491 0.2788 -3.7006 + 28.000 0.2447 0.2841 -3.7714 + 29.000 0.2414 0.2871 -3.7894 + 30.000 0.2393 0.2898 -3.8115 + 40.000 0.1968 0.3277 -2.6421 + 50.000 0.1614 0.3683 -2.6421 + 60.000 0.1243 0.4069 -2.6421 + 70.000 0.0837 0.4389 -2.6421 + 80.000 0.0412 0.4607 -2.6421 + 90.000 0.0000 0.4700 -2.6421 + 100.000 -0.0288 0.4607 -2.6421 + 110.000 -0.0586 0.4389 -2.6421 + 120.000 -0.0870 0.4069 -2.6421 + 130.000 -0.1130 0.3683 -2.6421 + 140.000 -0.1378 0.3277 -2.6421 + 150.000 -0.1675 0.2898 -2.6421 + 160.000 -0.1117 0.2589 -2.6421 + 170.000 -0.0558 0.2481 -2.6421 + 180.000 0.0000 0.2481 -2.6421 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 69 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.5519 -2.6421 + -170.000 0.0585 0.5519 -2.6421 + -160.000 0.1170 0.5606 -2.6421 + -150.000 0.1756 0.5916 -2.6421 + -140.000 0.1427 0.6298 -2.6421 + -130.000 0.1159 0.6706 -2.6421 + -120.000 0.0885 0.7095 -2.6421 + -110.000 0.0593 0.7419 -2.6421 + -100.000 0.0290 0.7641 -2.6421 + -90.000 0.0000 0.7738 -2.6421 + -80.000 -0.0290 0.7641 -2.6421 + -70.000 -0.0593 0.7419 -2.6421 + -60.000 -0.0885 0.7095 -2.6421 + -50.000 -0.1159 0.6706 -2.6421 + -40.000 -0.1427 0.6298 -2.6421 + -30.000 -0.1756 0.5916 -2.6421 + -20.000 -0.1283 0.5722 -2.6421 + -10.000 -0.1157 0.5529 -2.9039 + -9.000 -0.1073 0.5525 -2.8553 + -8.000 -0.1038 0.5521 -2.8178 + -7.000 -0.0886 0.5519 -2.7624 + -6.000 -0.0700 0.5518 -2.7151 + -5.000 -0.0503 0.5516 -2.6793 + -4.000 -0.0293 0.5515 -2.6454 + -3.000 -0.0081 0.5514 -2.6240 + -1.000 0.0355 0.5513 -2.6411 + 0.000 0.0575 0.5513 -2.6574 + 1.000 0.0791 0.5513 -2.6737 + 2.000 0.1010 0.5513 -2.6904 + 5.000 0.1606 0.5516 -2.7421 + 6.000 0.1748 0.5518 -2.7605 + 7.000 0.1845 0.5521 -2.7774 + 9.000 0.2027 0.5527 -2.8344 + 10.000 0.2063 0.5535 -2.8582 + 11.000 0.2125 0.5542 -2.8904 + 12.000 0.2152 0.5553 -2.9314 + 13.000 0.2203 0.5564 -2.9780 + 14.000 0.2255 0.5576 -3.0290 + 15.000 0.2316 0.5588 -3.0844 + 16.000 0.2365 0.5602 -3.1417 + 17.000 0.2415 0.5617 -3.2040 + 18.000 0.2457 0.5633 -3.2661 + 19.000 0.2499 0.5651 -3.3298 + 20.000 0.2526 0.5671 -3.3930 + 21.000 0.2554 0.5692 -3.4574 + 22.000 0.2578 0.5713 -3.5243 + 23.000 0.2586 0.5737 -3.5852 + 24.000 0.2610 0.5758 -3.6592 + 25.000 0.2612 0.5783 -3.7205 + 26.000 0.2613 0.5806 -3.7805 + 27.000 0.2606 0.5831 -3.8336 + 28.000 0.2592 0.5857 -3.8789 + 29.000 0.2538 0.5888 -3.8910 + 30.000 0.2508 0.5916 -3.9145 + 40.000 0.2038 0.6298 -2.6421 + 50.000 0.1655 0.6706 -2.6421 + 60.000 0.1265 0.7095 -2.6421 + 70.000 0.0847 0.7419 -2.6421 + 80.000 0.0414 0.7641 -2.6421 + 90.000 0.0000 0.7738 -2.6421 + 100.000 -0.0290 0.7641 -2.6421 + 110.000 -0.0593 0.7419 -2.6421 + 120.000 -0.0885 0.7095 -2.6421 + 130.000 -0.1159 0.6706 -2.6421 + 140.000 -0.1427 0.6298 -2.6421 + 150.000 -0.1756 0.5916 -2.6421 + 160.000 -0.1170 0.5606 -2.6421 + 170.000 -0.0585 0.5519 -2.6421 + 180.000 0.0000 0.5519 -2.6421 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 71 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.5765 -2.6421 + -170.000 0.0607 0.5765 -2.6421 + -160.000 0.1214 0.5836 -2.6421 + -150.000 0.1821 0.6147 -2.6421 + -140.000 0.1467 0.6531 -2.6421 + -130.000 0.1182 0.6942 -2.6421 + -120.000 0.0898 0.7333 -2.6421 + -110.000 0.0598 0.7660 -2.6421 + -100.000 0.0291 0.7885 -2.6421 + -90.000 0.0000 0.7984 -2.6421 + -80.000 -0.0291 0.7885 -2.6421 + -70.000 -0.0598 0.7660 -2.6421 + -60.000 -0.0898 0.7333 -2.6421 + -50.000 -0.1182 0.6942 -2.6421 + -40.000 -0.1467 0.6531 -2.6421 + -30.000 -0.1821 0.6147 -2.6421 + -20.000 -0.1332 0.5960 -2.6421 + -10.000 -0.1205 0.5773 -2.9139 + -9.000 -0.1129 0.5769 -2.8656 + -8.000 -0.1057 0.5766 -2.8211 + -7.000 -0.0889 0.5765 -2.7629 + -6.000 -0.0703 0.5763 -2.7155 + -5.000 -0.0499 0.5762 -2.6789 + -4.000 -0.0288 0.5761 -2.6448 + -3.000 -0.0075 0.5760 -2.6237 + -2.000 0.0142 0.5759 -2.6263 + -1.000 0.0362 0.5758 -2.6416 + 0.000 0.0582 0.5758 -2.6578 + 1.000 0.0803 0.5758 -2.6745 + 2.000 0.1017 0.5759 -2.6909 + 4.000 0.1425 0.5760 -2.7255 + 5.000 0.1601 0.5762 -2.7421 + 6.000 0.1754 0.5765 -2.7596 + 7.000 0.1869 0.5766 -2.7798 + 8.000 0.1980 0.5768 -2.8088 + 9.000 0.2042 0.5773 -2.8362 + 10.000 0.2107 0.5779 -2.8643 + 11.000 0.2150 0.5787 -2.8954 + 12.000 0.2204 0.5796 -2.9422 + 13.000 0.2252 0.5806 -2.9891 + 14.000 0.2320 0.5817 -3.0455 + 15.000 0.2374 0.5829 -3.1009 + 16.000 0.2428 0.5842 -3.1603 + 17.000 0.2476 0.5857 -3.2240 + 19.000 0.2555 0.5891 -3.3512 + 20.000 0.2614 0.5906 -3.4288 + 21.000 0.2636 0.5927 -3.4927 + 22.000 0.2650 0.5949 -3.5583 + 23.000 0.2658 0.5973 -3.6225 + 24.000 0.2669 0.5996 -3.6923 + 25.000 0.2674 0.6019 -3.7579 + 26.000 0.2670 0.6044 -3.8169 + 27.000 0.2657 0.6069 -3.8686 + 28.000 0.2642 0.6095 -3.9160 + 29.000 0.2624 0.6121 -3.9580 + 30.000 0.2601 0.6147 -3.9922 + 40.000 0.2095 0.6531 -2.6421 + 50.000 0.1689 0.6942 -2.6421 + 60.000 0.1283 0.7333 -2.6421 + 70.000 0.0854 0.7660 -2.6421 + 80.000 0.0416 0.7885 -2.6421 + 90.000 0.0000 0.7984 -2.6421 + 100.000 -0.0291 0.7885 -2.6421 + 110.000 -0.0598 0.7660 -2.6421 + 120.000 -0.0898 0.7333 -2.6421 + 130.000 -0.1182 0.6942 -2.6421 + 140.000 -0.1467 0.6531 -2.6421 + 150.000 -0.1821 0.6147 -2.6421 + 160.000 -0.1214 0.5836 -2.6421 + 170.000 -0.0607 0.5765 -2.6421 + 180.000 0.0000 0.5765 -2.6421 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 62 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.5765 -2.6421 + -170.000 0.0727 0.5765 -2.6421 + -160.000 0.1455 0.5865 -2.6421 + -150.000 0.1715 0.6174 -2.6421 + -140.000 0.1402 0.6554 -2.6421 + -130.000 0.1144 0.6961 -2.6421 + -120.000 0.0878 0.7348 -2.6421 + -110.000 0.0589 0.7670 -2.6421 + -100.000 0.0289 0.7890 -2.6421 + -90.000 0.0000 0.7984 -2.6421 + -80.000 -0.0289 0.7890 -2.6421 + -70.000 -0.0589 0.7670 -2.6421 + -60.000 -0.0878 0.7348 -2.6421 + -50.000 -0.1144 0.6961 -2.6421 + -40.000 -0.1402 0.6554 -2.6421 + -30.000 -0.1715 0.6174 -2.6421 + -20.000 -0.1503 0.5939 -2.6421 + -10.000 -0.1223 0.5772 -2.9191 + -9.000 -0.1172 0.5767 -2.8738 + -8.000 -0.1072 0.5765 -2.8237 + -5.000 -0.0498 0.5762 -2.6788 + -4.000 -0.0287 0.5761 -2.6447 + -3.000 -0.0071 0.5760 -2.6217 + -2.000 0.0146 0.5759 -2.6265 + -1.000 0.0366 0.5758 -2.6418 + 0.000 0.0588 0.5758 -2.6582 + 1.000 0.0806 0.5758 -2.6747 + 2.000 0.1019 0.5758 -2.6912 + 3.000 0.1229 0.5759 -2.7082 + 4.000 0.1424 0.5761 -2.7238 + 6.000 0.1765 0.5764 -2.7594 + 7.000 0.1903 0.5765 -2.7828 + 8.000 0.2007 0.5767 -2.8120 + 9.000 0.2064 0.5772 -2.8389 + 11.000 0.2172 0.5785 -2.8998 + 12.000 0.2241 0.5793 -2.9500 + 13.000 0.2312 0.5802 -3.0035 + 15.000 0.2438 0.5823 -3.1186 + 16.000 0.2491 0.5836 -3.1799 + 17.000 0.2546 0.5849 -3.2469 + 18.000 0.2582 0.5865 -3.3095 + 19.000 0.2624 0.5882 -3.3777 + 20.000 0.2652 0.5901 -3.4441 + 22.000 0.2683 0.5945 -3.5738 + 25.000 0.2704 0.6015 -3.7758 + 26.000 0.2702 0.6039 -3.8370 + 30.000 0.2450 0.6174 -3.5690 + 40.000 0.2003 0.6554 -2.6421 + 50.000 0.1634 0.6961 -2.6421 + 60.000 0.1254 0.7348 -2.6421 + 70.000 0.0842 0.7670 -2.6421 + 80.000 0.0413 0.7890 -2.6421 + 90.000 0.0000 0.7984 -2.6421 + 100.000 -0.0289 0.7890 -2.6421 + 110.000 -0.0589 0.7670 -2.6421 + 120.000 -0.0878 0.7348 -2.6421 + 130.000 -0.1144 0.6961 -2.6421 + 140.000 -0.1402 0.6554 -2.6421 + 150.000 -0.1715 0.6174 -2.6421 + 160.000 -0.1455 0.5865 -2.6421 + 170.000 -0.0727 0.5765 -2.6421 + 180.000 0.0000 0.5765 -2.6421 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 67 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.5765 -2.6421 + -170.000 0.0628 0.5765 -2.6421 + -160.000 0.1256 0.5819 -2.6421 + -150.000 0.1883 0.6132 -2.6421 + -140.000 0.1505 0.6517 -2.6421 + -130.000 0.1204 0.6930 -2.6421 + -120.000 0.0910 0.7324 -2.6421 + -110.000 0.0603 0.7653 -2.6421 + -100.000 0.0292 0.7882 -2.6421 + -90.000 0.0000 0.7984 -2.6421 + -80.000 -0.0292 0.7882 -2.6421 + -70.000 -0.0603 0.7653 -2.6421 + -60.000 -0.0910 0.7324 -2.6421 + -50.000 -0.1204 0.6930 -2.6421 + -40.000 -0.1505 0.6517 -2.6421 + -30.000 -0.1883 0.6132 -2.6421 + -20.000 -0.1368 0.5952 -2.6421 + -10.000 -0.1219 0.5772 -2.9149 + -9.000 -0.1226 0.5766 -2.8845 + -8.000 -0.1085 0.5765 -2.8260 + -6.000 -0.0705 0.5762 -2.7163 + -4.000 -0.0286 0.5760 -2.6446 + -3.000 -0.0069 0.5760 -2.6219 + -2.000 0.0149 0.5759 -2.6267 + -1.000 0.0370 0.5758 -2.6420 + 0.000 0.0591 0.5758 -2.6583 + 1.000 0.0807 0.5758 -2.6748 + 2.000 0.1020 0.5758 -2.6915 + 4.000 0.1420 0.5761 -2.7229 + 5.000 0.1598 0.5763 -2.7401 + 6.000 0.1771 0.5764 -2.7606 + 7.000 0.1940 0.5765 -2.7861 + 8.000 0.2019 0.5767 -2.8134 + 9.000 0.2093 0.5771 -2.8426 + 10.000 0.2125 0.5778 -2.8638 + 11.000 0.2210 0.5783 -2.9073 + 12.000 0.2274 0.5791 -2.9570 + 13.000 0.2343 0.5800 -3.0108 + 14.000 0.2412 0.5809 -3.0686 + 16.000 0.2529 0.5832 -3.1916 + 17.000 0.2573 0.5847 -3.2559 + 18.000 0.2618 0.5862 -3.3219 + 19.000 0.2653 0.5879 -3.3887 + 20.000 0.2679 0.5898 -3.4550 + 21.000 0.2693 0.5919 -3.5174 + 24.000 0.2762 0.5982 -3.7432 + 25.000 0.2769 0.6005 -3.8133 + 26.000 0.2769 0.6029 -3.8791 + 27.000 0.2762 0.6053 -3.9388 + 28.000 0.2745 0.6078 -3.9894 + 29.000 0.2719 0.6105 -4.0313 + 30.000 0.2691 0.6132 -4.0663 + 40.000 0.2150 0.6517 -2.6421 + 50.000 0.1721 0.6930 -2.6421 + 60.000 0.1300 0.7324 -2.6421 + 70.000 0.0862 0.7653 -2.6421 + 80.000 0.0418 0.7882 -2.6421 + 90.000 0.0000 0.7984 -2.6421 + 100.000 -0.0292 0.7882 -2.6421 + 110.000 -0.0603 0.7653 -2.6421 + 120.000 -0.0910 0.7324 -2.6421 + 130.000 -0.1204 0.6930 -2.6421 + 140.000 -0.1505 0.6517 -2.6421 + 150.000 -0.1883 0.6132 -2.6421 + 160.000 -0.1256 0.5819 -2.6421 + 170.000 -0.0628 0.5765 -2.6421 + 180.000 0.0000 0.5765 -2.6421 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 68 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.5765 -2.6421 + -170.000 0.0661 0.5765 -2.6421 + -160.000 0.1322 0.5825 -2.6421 + -150.000 0.1869 0.6137 -2.6421 + -140.000 0.1496 0.6521 -2.6421 + -130.000 0.1199 0.6934 -2.6421 + -120.000 0.0907 0.7327 -2.6421 + -110.000 0.0602 0.7655 -2.6421 + -100.000 0.0292 0.7883 -2.6421 + -90.000 0.0000 0.7984 -2.6421 + -80.000 -0.0292 0.7883 -2.6421 + -70.000 -0.0602 0.7655 -2.6421 + -60.000 -0.0907 0.7327 -2.6421 + -50.000 -0.1199 0.6934 -2.6421 + -40.000 -0.1496 0.6521 -2.6421 + -30.000 -0.1869 0.6137 -2.6421 + -20.000 -0.1421 0.5945 -2.6421 + -10.000 -0.1243 0.5770 -2.9202 + -7.000 -0.0904 0.5763 -2.7654 + -6.000 -0.0703 0.5762 -2.7143 + -5.000 -0.0498 0.5761 -2.6788 + -4.000 -0.0285 0.5760 -2.6445 + -3.000 -0.0068 0.5760 -2.6224 + -2.000 0.0151 0.5759 -2.6268 + -1.000 0.0372 0.5758 -2.6421 + 0.000 0.0592 0.5758 -2.6584 + 1.000 0.0809 0.5758 -2.6749 + 2.000 0.1021 0.5758 -2.6908 + 3.000 0.1228 0.5759 -2.7064 + 4.000 0.1421 0.5761 -2.7236 + 5.000 0.1599 0.5762 -2.7406 + 6.000 0.1783 0.5763 -2.7617 + 7.000 0.1954 0.5765 -2.7874 + 8.000 0.2032 0.5767 -2.8148 + 10.000 0.2152 0.5776 -2.8684 + 11.000 0.2233 0.5782 -2.9119 + 12.000 0.2310 0.5789 -2.9648 + 13.000 0.2383 0.5797 -3.0203 + 14.000 0.2437 0.5807 -3.0748 + 15.000 0.2498 0.5818 -3.1353 + 17.000 0.2600 0.5844 -3.2646 + 18.000 0.2642 0.5859 -3.3301 + 19.000 0.2676 0.5876 -3.3976 + 20.000 0.2694 0.5896 -3.4608 + 22.000 0.2766 0.5933 -3.6125 + 23.000 0.2780 0.5955 -3.6858 + 24.000 0.2791 0.5978 -3.7589 + 25.000 0.2796 0.6001 -3.8288 + 26.000 0.2794 0.6025 -3.8941 + 27.000 0.2781 0.6050 -3.9509 + 28.000 0.2762 0.6076 -4.0012 + 29.000 0.2739 0.6102 -4.0458 + 30.000 0.2671 0.6137 -3.9598 + 40.000 0.2137 0.6521 -2.6421 + 50.000 0.1713 0.6934 -2.6421 + 60.000 0.1296 0.7327 -2.6421 + 70.000 0.0860 0.7655 -2.6421 + 80.000 0.0417 0.7883 -2.6421 + 90.000 0.0000 0.7984 -2.6421 + 100.000 -0.0292 0.7883 -2.6421 + 110.000 -0.0602 0.7655 -2.6421 + 120.000 -0.0907 0.7327 -2.6421 + 130.000 -0.1199 0.6934 -2.6421 + 140.000 -0.1496 0.6521 -2.6421 + 150.000 -0.1869 0.6137 -2.6421 + 160.000 -0.1322 0.5825 -2.6421 + 170.000 -0.0661 0.5765 -2.6421 + 180.000 0.0000 0.5765 -2.6421 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.000 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 64 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.000 0.0000 0.5765 -2.6421 + -170.000 0.0637 0.5765 -2.6421 + -160.000 0.1274 0.5812 -2.6421 + -150.000 0.1912 0.6125 -2.6421 + -140.000 0.1522 0.6511 -2.6421 + -130.000 0.1215 0.6925 -2.6421 + -120.000 0.0915 0.7320 -2.6421 + -110.000 0.0606 0.7651 -2.6421 + -100.000 0.0293 0.7880 -2.6421 + -90.000 0.0000 0.7984 -2.6421 + -80.000 -0.0293 0.7880 -2.6421 + -70.000 -0.0606 0.7651 -2.6421 + -60.000 -0.0915 0.7320 -2.6421 + -50.000 -0.1215 0.6925 -2.6421 + -40.000 -0.1522 0.6511 -2.6421 + -30.000 -0.1912 0.6125 -2.6421 + -20.000 -0.1399 0.5947 -2.6421 + -10.000 -0.1267 0.5770 -2.9252 + -9.000 -0.1232 0.5766 -2.8832 + -8.000 -0.1096 0.5764 -2.8283 + -6.000 -0.0703 0.5762 -2.7138 + -5.000 -0.0497 0.5761 -2.6788 + -4.000 -0.0285 0.5760 -2.6445 + -3.000 -0.0066 0.5759 -2.6225 + -2.000 0.0153 0.5759 -2.6269 + -1.000 0.0373 0.5758 -2.6422 + 0.000 0.0594 0.5758 -2.6585 + 1.000 0.0807 0.5758 -2.6749 + 2.000 0.1021 0.5758 -2.6907 + 3.000 0.1226 0.5759 -2.7061 + 5.000 0.1605 0.5762 -2.7412 + 6.000 0.1789 0.5763 -2.7623 + 7.000 0.1967 0.5764 -2.7887 + 8.000 0.2039 0.5767 -2.8156 + 11.000 0.2254 0.5781 -2.9160 + 12.000 0.2331 0.5788 -2.9692 + 14.000 0.2475 0.5804 -3.0842 + 16.000 0.2573 0.5828 -3.2053 + 18.000 0.2662 0.5857 -3.3369 + 21.000 0.2770 0.5909 -3.5511 + 22.000 0.2788 0.5930 -3.6222 + 23.000 0.2804 0.5952 -3.6977 + 24.000 0.2812 0.5975 -3.7705 + 25.000 0.2815 0.5998 -3.8400 + 26.000 0.2807 0.6023 -3.9023 + 27.000 0.2794 0.6048 -3.9597 + 28.000 0.2777 0.6073 -4.0122 + 29.000 0.2757 0.6099 -4.0591 + 30.000 0.2731 0.6125 -4.0985 + 40.000 0.2174 0.6511 -2.6421 + 50.000 0.1735 0.6925 -2.6421 + 60.000 0.1308 0.7320 -2.6421 + 70.000 0.0865 0.7651 -2.6421 + 80.000 0.0419 0.7880 -2.6421 + 90.000 0.0000 0.7984 -2.6421 + 100.000 -0.0293 0.7880 -2.6421 + 110.000 -0.0606 0.7651 -2.6421 + 120.000 -0.0915 0.7320 -2.6421 + 130.000 -0.1215 0.6925 -2.6421 + 140.000 -0.1522 0.6511 -2.6421 + 150.000 -0.1912 0.6125 -2.6421 + 160.000 -0.1274 0.5812 -2.6421 + 170.000 -0.0637 0.5765 -2.6421 + 180.000 0.0000 0.5765 -2.6421 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_0864_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_0864_coords.txt new file mode 100644 index 00000000..8a9382a1 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_0864_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_0864 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.071897 + 0.027091 0.142126 + 0.060263 0.208964 + 0.105430 0.270115 + 0.161359 0.323830 + 0.226526 0.368470 + 0.299152 0.402651 + 0.377257 0.425156 + 0.458710 0.435236 + 0.541290 0.432906 + 0.622743 0.418526 + 0.700848 0.392758 + 0.773474 0.356678 + 0.838641 0.311513 + 0.894570 0.258619 + 0.939737 0.199450 + 0.972909 0.135539 + 0.993181 0.068594 + 1.000000 0.000000 + 0.993181 -0.068161 + 0.972909 -0.134227 + 0.939737 -0.197056 + 0.894570 -0.255087 + 0.838641 -0.306904 + 0.773474 -0.351143 + 0.700848 -0.386540 + 0.622743 -0.411920 + 0.541290 -0.426222 + 0.458710 -0.428757 + 0.377257 -0.419101 + 0.299152 -0.397194 + 0.226526 -0.363795 + 0.161359 -0.320050 + 0.105430 -0.267316 + 0.060263 -0.207125 + 0.027091 -0.141176 + 0.006819 -0.071509 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_1000.dat b/example/MHK_RM1_Floating/Airfoils/NACA6_1000.dat new file mode 100644 index 00000000..7c3e8471 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_1000.dat @@ -0,0 +1,108 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA6_1000 airfoil, data based on values used for the design of the RM1 tidal current turbine. +! line +! line +! ------------------------------------------------------------------------------ +"default" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1.0 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA6_1000_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 7 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 2.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.00 0.0 0.3 -3.0 + 0.00 0.0 0.3 -3.0 + 180.00 0.0 0.3 -3.0 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ + 4.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.00 0.0 0.67 -3.0 + 0.00 0.0 0.67 -3.0 + 180.00 0.0 0.67 -3.0 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ + 6.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.00 0.0 0.7 -3.0 + 0.00 0.0 0.7 -3.0 + 180.00 0.0 0.7 -3.0 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ + 8.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.00 0.0 0.7 -3.0 + 0.00 0.0 0.7 -3.0 + 180.00 0.0 0.7 -3.0 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ + 10.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.00 0.0 0.7 -3.0 + 0.00 0.0 0.7 -3.0 + 180.00 0.0 0.7 -3.0 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ + 12.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.00 0.0 0.7 -3.0 + 0.00 0.0 0.7 -3.0 + 180.00 0.0 0.7 -3.0 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ + 14.0 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cpmin +! (deg) (-) (-) (-) + -180.00 0.0 0.7 -3.0 + 0.00 0.0 0.7 -3.0 + 180.00 0.0 0.7 -3.0 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/Airfoils/NACA6_1000_coords.txt b/example/MHK_RM1_Floating/Airfoils/NACA6_1000_coords.txt new file mode 100644 index 00000000..e9876cf7 --- /dev/null +++ b/example/MHK_RM1_Floating/Airfoils/NACA6_1000_coords.txt @@ -0,0 +1,47 @@ + 40 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.25 0 +! coordinates of airfoil shape +! NACA6_1000 Airfoil +! x/c y/c + 0.000000 0.000000 + 0.006819 0.082442 + 0.027091 0.162359 + 0.060263 0.237976 + 0.105430 0.307106 + 0.161359 0.367865 + 0.226526 0.418583 + 0.299152 0.457883 + 0.377257 0.484712 + 0.458710 0.498283 + 0.541290 0.498283 + 0.622743 0.484712 + 0.700848 0.457883 + 0.773474 0.418583 + 0.838641 0.367865 + 0.894570 0.307106 + 0.939737 0.237976 + 0.972909 0.162359 + 0.993181 0.082442 + 1.000000 0.000000 + 0.993181 -0.082442 + 0.972909 -0.162359 + 0.939737 -0.237976 + 0.894570 -0.307106 + 0.838641 -0.367865 + 0.773474 -0.418583 + 0.700848 -0.457883 + 0.622743 -0.484712 + 0.541290 -0.498283 + 0.458710 -0.498283 + 0.377257 -0.484712 + 0.299152 -0.457883 + 0.226526 -0.418583 + 0.161359 -0.367865 + 0.105430 -0.307106 + 0.060263 -0.237976 + 0.027091 -0.162359 + 0.006819 -0.082442 + 0.000000 0.000000 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/LICENSE b/example/MHK_RM1_Floating/LICENSE new file mode 100644 index 00000000..8dada3ed --- /dev/null +++ b/example/MHK_RM1_Floating/LICENSE @@ -0,0 +1,201 @@ + Apache License + Version 2.0, January 2004 + http://www.apache.org/licenses/ + + TERMS AND CONDITIONS FOR USE, REPRODUCTION, AND DISTRIBUTION + + 1. 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We also recommend that a + file or class name and description of purpose be included on the + same "printed page" as the copyright notice for easier + identification within third-party archives. + + Copyright {yyyy} {name of copyright owner} + + Licensed under the Apache License, Version 2.0 (the "License"); + you may not use this file except in compliance with the License. + You may obtain a copy of the License at + + http://www.apache.org/licenses/LICENSE-2.0 + + Unless required by applicable law or agreed to in writing, software + distributed under the License is distributed on an "AS IS" BASIS, + WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied. + See the License for the specific language governing permissions and + limitations under the License. diff --git a/example/MHK_RM1_Floating/MHK_RM1_AeroDyn_Blade.dat b/example/MHK_RM1_Floating/MHK_RM1_AeroDyn_Blade.dat new file mode 100644 index 00000000..1998b6e8 --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_AeroDyn_Blade.dat @@ -0,0 +1,38 @@ +------- AERODYN v15.00.* BLADE DEFINITION INPUT FILE ------------------------------------- +Floating MHK turbine hydrodynamic blade input properties, based on the RM1 tidal current rotor +====== Blade Properties ================================================================= +32 NumBlNds - Number of blade nodes used in the analysis (-) +BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID BlCb BlCenBn BlCenBt +(m) (m) (m) (deg) (deg) (m) (-) (-) (m) (m) +0.000 0.00 0.00 0.00 12.86 0.800 1 0.9956 0.0000 0.00000 +0.150 0.00 0.00 0.00 12.86 0.800 1 0.9956 0.0000 0.00000 +0.450 0.00 0.00 0.00 12.86 0.894 2 0.8572 0.0023 0.01458 +0.750 0.00 0.00 0.00 12.86 1.118 3 0.6118 0.0082 0.05128 +1.050 0.00 0.00 0.00 12.86 1.386 4 0.4145 0.0153 0.12252 +1.350 0.00 0.00 0.00 12.86 1.610 5 0.2873 0.0217 0.16820 +1.650 0.00 0.00 0.00 12.86 1.704 6 0.2287 0.0250 0.17802 +1.950 0.00 0.00 0.00 11.54 1.662 7 0.2099 0.0250 0.15896 +2.250 0.00 0.00 0.00 10.44 1.619 8 0.1966 0.0247 0.14317 +2.550 0.00 0.00 0.00 9.50 1.577 9 0.1870 0.0245 0.12821 +2.850 0.00 0.00 0.00 8.71 1.534 9 0.1870 0.0238 0.12472 +3.150 0.00 0.00 0.00 8.02 1.492 9 0.1870 0.0232 0.12136 +3.450 0.00 0.00 0.00 7.43 1.450 9 0.1870 0.0225 0.11790 +3.750 0.00 0.00 0.00 6.91 1.407 9 0.1870 0.0218 0.11441 +4.050 0.00 0.00 0.00 6.45 1.365 9 0.1870 0.0212 0.11105 +4.350 0.00 0.00 0.00 6.04 1.322 9 0.1870 0.0205 0.10756 +4.650 0.00 0.00 0.00 5.68 1.279 9 0.1870 0.0198 0.10397 +4.950 0.00 0.00 0.00 5.35 1.235 9 0.1870 0.0192 0.10045 +5.250 0.00 0.00 0.00 5.05 1.192 9 0.1870 0.0185 0.09696 +5.550 0.00 0.00 0.00 4.77 1.148 9 0.1870 0.0178 0.09334 +5.850 0.00 0.00 0.00 4.51 1.103 9 0.1870 0.0171 0.08969 +6.150 0.00 0.00 0.00 4.26 1.058 9 0.1870 0.0164 0.08604 +6.450 0.00 0.00 0.00 4.03 1.012 9 0.1870 0.0157 0.08226 +6.750 0.00 0.00 0.00 3.80 0.966 9 0.1870 0.0150 0.07858 +7.050 0.00 0.00 0.00 3.57 0.920 9 0.1870 0.0143 0.07480 +7.350 0.00 0.00 0.00 3.35 0.872 9 0.1870 0.0135 0.07096 +7.650 0.00 0.00 0.00 3.13 0.824 9 0.1870 0.0128 0.06702 +7.950 0.00 0.00 0.00 2.90 0.776 9 0.1870 0.0120 0.06308 +8.250 0.00 0.00 0.00 2.67 0.726 9 0.1870 0.0113 0.05908 +8.550 0.00 0.00 0.00 2.43 0.676 9 0.1870 0.0105 0.05498 +8.850 0.00 0.00 0.00 2.18 0.626 9 0.1870 0.0097 0.05088 +9.000 0.00 0.00 0.00 2.18 0.626 9 0.1870 0.0097 0.05088 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/MHK_RM1_ElastoDyn_Blade.dat b/example/MHK_RM1_Floating/MHK_RM1_ElastoDyn_Blade.dat new file mode 100644 index 00000000..df6ab8c8 --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_ElastoDyn_Blade.dat @@ -0,0 +1,107 @@ +------- ELASTODYN V1.00.* INDIVIDUAL BLADE INPUT FILE -------------------------- +Floating MHK turbine structural blade input properties, based on the RM1 tidal current rotor +---------------------- BLADE PARAMETERS ---------------------------------------- + 75 NBlInpSt - Number of blade input stations (-) + 1 BldFlDmp(1) - Blade flap mode #1 structural damping in percent of critical (%) + 1 BldFlDmp(2) - Blade flap mode #2 structural damping in percent of critical (%) + 1 BldEdDmp(1) - Blade edge mode #1 structural damping in percent of critical (%) +---------------------- BLADE ADJUSTMENT FACTORS -------------------------------- + 1 FlStTunr(1) - Blade flapwise modal stiffness tuner, 1st mode (-) + 1 FlStTunr(2) - Blade flapwise modal stiffness tuner, 2nd mode (-) + 2.5 AdjBlMs - Factor to adjust blade mass density (-) + 1.0E-05 AdjFlSt - Factor to adjust blade flap stiffness (-) + 1.0E-05 AdjEdSt - Factor to adjust blade edge stiffness (-) +---------------------- DISTRIBUTED BLADE PROPERTIES ---------------------------- +BlFract PitchAxis StrcTwst BMassDen FlpStff EdgStff +(-) (-) (deg) (kg/m) (Nm^2) (Nm^2) +0.0000 0.5000 12.860 818.68 2.43E+14 2.52E+14 +0.0083 0.4953 12.860 833.60 2.47E+14 2.69E+14 +0.0167 0.4907 12.860 846.44 2.47E+14 2.84E+14 +0.0250 0.4860 12.860 858.68 2.46E+14 3.00E+14 +0.0333 0.4813 12.860 870.32 2.44E+14 3.15E+14 +0.0417 0.4701 12.860 900.64 2.50E+14 3.59E+14 +0.0500 0.4590 12.860 932.64 2.49E+14 4.03E+14 +0.0583 0.4478 12.860 681.32 1.70E+14 1.12E+14 +0.0667 0.4366 12.860 628.00 1.48E+14 1.11E+14 +0.0750 0.4233 12.860 575.28 1.30E+14 1.10E+14 +0.0833 0.4100 12.860 528.96 1.12E+14 1.07E+14 +0.0917 0.3967 12.860 458.92 8.82E+13 9.56E+13 +0.1000 0.3834 12.860 401.60 6.72E+13 8.55E+13 +0.1083 0.3722 12.860 411.16 6.45E+13 9.15E+13 +0.1167 0.3611 12.860 410.28 6.00E+13 9.53E+13 +0.1250 0.3499 12.860 415.36 5.62E+13 1.01E+14 +0.1333 0.3387 12.860 421.00 5.17E+13 1.06E+14 +0.1417 0.3340 12.860 421.28 4.94E+13 1.08E+14 +0.1500 0.3294 12.860 421.40 4.70E+13 1.10E+14 +0.1583 0.3247 12.860 424.96 4.45E+13 1.12E+14 +0.1667 0.3200 12.860 435.48 4.30E+13 1.16E+14 +0.1750 0.3200 12.530 428.40 4.09E+13 1.13E+14 +0.1833 0.3200 12.200 423.88 3.89E+13 1.10E+14 +0.1917 0.3200 11.870 435.68 3.84E+13 1.15E+14 +0.2000 0.3200 11.540 430.60 3.62E+13 1.12E+14 +0.2083 0.3200 11.265 434.52 3.57E+13 1.11E+14 +0.2167 0.3200 10.990 430.28 3.41E+13 1.09E+14 +0.2250 0.3200 10.715 426.04 3.26E+13 1.06E+14 +0.2333 0.3200 10.440 421.84 3.11E+13 1.03E+14 +0.2500 0.3200 9.970 415.00 2.91E+13 9.84E+13 +0.2667 0.3200 9.500 411.20 2.72E+13 9.54E+13 +0.2833 0.3200 9.105 395.88 2.54E+13 8.96E+13 +0.3000 0.3200 8.710 390.40 2.43E+13 8.59E+13 +0.3167 0.3200 8.365 377.84 2.26E+13 8.06E+13 +0.3333 0.3200 8.020 362.44 2.15E+13 7.34E+13 +0.3500 0.3200 7.725 347.48 2.00E+13 6.87E+13 +0.3667 0.3200 7.430 335.60 1.85E+13 6.42E+13 +0.3833 0.3200 7.170 330.64 1.77E+13 6.14E+13 +0.4000 0.3200 6.910 318.96 1.63E+13 5.72E+13 +0.4167 0.3200 6.680 302.84 1.50E+13 5.33E+13 +0.4333 0.3200 6.450 298.24 1.43E+13 5.09E+13 +0.4500 0.3200 6.245 287.12 1.32E+13 4.73E+13 +0.4667 0.3200 6.040 267.24 1.19E+13 4.12E+13 +0.4833 0.3200 5.860 256.68 1.09E+13 3.81E+13 +0.5000 0.3200 5.680 249.96 1.04E+13 3.62E+13 +0.5167 0.3200 5.515 239.68 9.42E+12 3.33E+13 +0.5333 0.3200 5.350 227.76 8.54E+12 3.06E+13 +0.5500 0.3200 5.200 215.64 7.73E+12 2.81E+13 +0.5667 0.3200 5.050 206.16 6.97E+12 2.58E+13 +0.5833 0.3200 4.910 188.80 6.17E+12 2.17E+13 +0.6000 0.3200 4.770 179.80 5.51E+12 1.97E+13 +0.6167 0.3200 4.640 176.28 5.19E+12 1.85E+13 +0.6333 0.3200 4.510 165.32 4.61E+12 1.68E+13 +0.6500 0.3200 4.385 156.80 4.07E+12 1.51E+13 +0.6667 0.3200 4.260 144.88 3.57E+12 1.36E+13 +0.6833 0.3200 4.145 136.80 3.11E+12 1.21E+13 +0.7000 0.3200 4.030 128.92 2.69E+12 1.08E+13 +0.7167 0.3200 3.915 119.36 2.31E+12 9.55E+12 +0.7333 0.3200 3.800 111.96 1.96E+12 8.42E+12 +0.7500 0.3200 3.685 103.00 1.65E+12 7.39E+12 +0.7667 0.3200 3.570 94.72 1.37E+12 6.45E+12 +0.7833 0.3200 3.460 87.96 1.12E+12 5.57E+12 +0.8000 0.3200 3.350 79.76 8.91E+11 4.77E+12 +0.8167 0.3200 3.240 73.52 6.93E+11 4.05E+12 +0.8333 0.3200 3.130 71.44 6.36E+11 3.72E+12 +0.8500 0.3200 3.015 64.00 4.76E+11 3.11E+12 +0.8667 0.3200 2.900 57.24 3.38E+11 2.56E+12 +0.8833 0.3200 2.785 50.36 2.19E+11 2.04E+12 +0.9000 0.3200 2.670 48.68 1.98E+11 1.84E+12 +0.9167 0.3200 2.550 47.00 1.78E+11 1.66E+12 +0.9333 0.3200 2.430 45.32 1.59E+11 1.49E+12 +0.9500 0.3200 2.305 46.76 1.98E+11 1.51E+12 +0.9667 0.3200 2.180 44.04 1.76E+11 1.34E+12 +0.9833 0.3200 2.060 42.28 1.56E+11 1.19E+12 +1.0000 0.3200 2.060 42.28 1.56E+11 1.19E+12 +---------------------- BLADE MODE SHAPES --------------------------------------- + 1.88070 BldFl1Sh(2) - Flap mode 1, coeff of x^2 +-1.44580 BldFl1Sh(3) - , coeff of x^3 + 0.71967 BldFl1Sh(4) - , coeff of x^4 +-0.03633 BldFl1Sh(5) - , coeff of x^5 +-0.11822 BldFl1Sh(6) - , coeff of x^6 +-5.52180 BldFl2Sh(2) - Flap mode 2, coeff of x^2 + 7.45710 BldFl2Sh(3) - , coeff of x^3 + 2.84170 BldFl2Sh(4) - , coeff of x^4 +-3.97820 BldFl2Sh(5) - , coeff of x^5 + 0.20116 BldFl2Sh(6) - , coeff of x^6 + 2.48090 BldEdgSh(2) - Edge mode 1, coeff of x^2 +-4.17160 BldEdgSh(3) - , coeff of x^3 + 5.03260 BldEdgSh(4) - , coeff of x^4 +-2.86170 BldEdgSh(5) - , coeff of x^5 + 0.51983 BldEdgSh(6) - , coeff of x^6 \ No newline at end of file diff --git a/example/MHK_RM1_Floating/MHK_RM1_Floating.fst b/example/MHK_RM1_Floating/MHK_RM1_Floating.fst new file mode 100644 index 00000000..5ce3a753 --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_Floating.fst @@ -0,0 +1,73 @@ +------- OpenFAST EXAMPLE INPUT FILE ------------------------------------------- +Floating MHK turbine, based on the RM1 tidal current rotor +---------------------- SIMULATION CONTROL -------------------------------------- +False Echo - Echo input data to .ech (flag) +"FATAL" AbortLevel - Error level when simulation should abort (string) {"WARNING", "SEVERE", "FATAL"} + 1 TMax - Total run time (s) + 0.01 DT - Recommended module time step (s) + 2 InterpOrder - Interpolation order for input/output time history (-) {1=linear, 2=quadratic} + 5 NumCrctn - Number of correction iterations (-) {0=explicit calculation, i.e., no corrections} + 99999 DT_UJac - Time between calls to get Jacobians (s) + 1000000 UJacSclFact - Scaling factor used in Jacobians (-) +---------------------- FEATURE SWITCHES AND FLAGS ------------------------------ + 1 CompElast - Compute structural dynamics (switch) {1=ElastoDyn; 2=ElastoDyn + BeamDyn for blades; 3=Simplified ElastoDyn} + 1 CompInflow - Compute inflow wind velocities (switch) {0=still air; 1=InflowWind; 2=external from ExtInflow} + 2 CompAero - Compute aerodynamic loads (switch) {0=None; 1=AeroDisk; 2=AeroDyn; 3=ExtLoads} + 0 CompServo - Compute control and electrical-drive dynamics (switch) {0=None; 1=ServoDyn} + 1 CompSeaSt - Compute sea state information (switch) {0=None; 1=SeaState} + 1 CompHydro - Compute hydrodynamic loads (switch) {0=None; 1=HydroDyn} + 0 CompSub - Compute sub-structural dynamics (switch) {0=None; 1=SubDyn; 2=External Platform MCKF} + 3 CompMooring - Compute mooring system (switch) {0=None; 1=MAP++; 2=FEAMooring; 3=MoorDyn; 4=OrcaFlex} + 0 CompIce - Compute ice loads (switch) {0=None; 1=IceFloe; 2=IceDyn} + 2 MHK - MHK turbine type (switch) {0=Not an MHK turbine; 1=Fixed MHK turbine; 2=Floating MHK turbine} +---------------------- ENVIRONMENTAL CONDITIONS -------------------------------- + 9.80665 Gravity - Gravitational acceleration (m/s^2) + 1.225 AirDens - Air density (kg/m^3) + 1025 WtrDens - Water density (kg/m^3) + 1.06E-06 KinVisc - Kinematic viscosity of working fluid (m^2/s) + 1500 SpdSound - Speed of sound in working fluid (m/s) + 101325 Patm - Atmospheric pressure (Pa) [used only for an MHK turbine cavitation check] + 2500 Pvap - Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check] + 50 WtrDpth - Water depth (m) + 0 MSL2SWL - Offset between still-water level and mean sea level (m) [positive upward] +---------------------- INPUT FILES --------------------------------------------- +"MHK_RM1_Floating_ElastoDyn.dat" EDFile - Name of file containing ElastoDyn input parameters (quoted string) +"unused" BDBldFile(1) - Name of file containing BeamDyn input parameters for blade 1 (quoted string) +"unused" BDBldFile(2) - Name of file containing BeamDyn input parameters for blade 2 (quoted string) +"unused" BDBldFile(3) - Name of file containing BeamDyn input parameters for blade 3 (quoted string) +"MHK_RM1_Floating_InflowWind.dat" InflowFile - Name of file containing inflow wind input parameters (quoted string) +"MHK_RM1_Floating_AeroDyn.dat" AeroFile - Name of file containing aerodynamic input parameters (quoted string) +"unused" ServoFile - Name of file containing control and electrical-drive input parameters (quoted string) +"SeaState.dat" SeaStFile - Name of file containing sea state input parameters (quoted string) +"MHK_RM1_Floating_HydroDyn.dat" HydroFile - Name of file containing hydrodynamic input parameters (quoted string) +"unused" SubFile - Name of file containing sub-structural input parameters (quoted string) +"MHK_RM1_Floating_MoorDyn.dat" MooringFile - Name of file containing mooring system input parameters (quoted string) +"unused" IceFile - Name of file containing ice input parameters (quoted string) +---------------------- OUTPUT -------------------------------------------------- +True SumPrint - Print summary data to ".sum" (flag) + 5 SttsTime - Amount of time between screen status messages (s) + 99999 ChkptTime - Amount of time between creating checkpoint files for potential restart (s) + 0.1 DT_Out - Time step for tabular output (s) (or "default") + 0 TStart - Time to begin tabular output (s) + 3 OutFileFmt - Format for tabular (time-marching) output file (switch) {1: text file [.out], 2: binary file [.outb], 3: both 1 and 2, 4: uncompressed binary [.outb, 5: both 1 and 4} +True TabDelim - Use tab delimiters in text tabular output file? (flag) {uses spaces if false} +"ES10.3E2" OutFmt - Format used for text tabular output, excluding the time channel. Resulting field should be 10 characters. (quoted string) +---------------------- LINEARIZATION ------------------------------------------- +False Linearize - Linearization analysis (flag) +False CalcSteady - Calculate a steady-state periodic operating point before linearization? [unused if Linearize=False] (flag) + 1 TrimCase - Controller parameter to be trimmed {1:yaw; 2:torque; 3:pitch} [used only if CalcSteady=True] (-) + 0.01 TrimTol - Tolerance for the rotational speed convergence [used only if CalcSteady=True] (-) + 0.01 TrimGain - Proportional gain for the rotational speed error (>0) [used only if CalcSteady=True] (rad/(rad/s) for yaw or pitch; Nm/(rad/s) for torque) + 0 Twr_Kdmp - Damping factor for the tower [used only if CalcSteady=True] (N/(m/s)) + 0 Bld_Kdmp - Damping factor for the blades [used only if CalcSteady=True] (N/(m/s)) + 0 NLinTimes - Number of times to linearize (-) [>=1] [unused if Linearize=False] + 0 LinTimes - List of times at which to linearize (s) [1 to NLinTimes] [used only when Linearize=True and CalcSteady=False] + 0 LinInputs - Inputs included in linearization (switch) {0=none; 1=standard; 2=all module inputs (debug)} [unused if Linearize=False] + 0 LinOutputs - Outputs included in linearization (switch) {0=none; 1=from OutList(s); 2=all module outputs (debug)} [unused if Linearize=False] +False LinOutJac - Include full Jacobians in linearization output (for debug) (flag) [unused if Linearize=False; used only if LinInputs=LinOutputs=2] +False LinOutMod - Write module-level linearization output files in addition to output for full system? (flag) [unused if Linearize=False] +---------------------- VISUALIZATION ------------------------------------------ + 0 WrVTK - VTK visualization data output: (switch) {0=none; 1=initialization data only; 2=animation; 3=mode shapes} + 1 VTK_type - Type of VTK visualization data: (switch) {1=surfaces; 2=basic meshes (lines/points); 3=all meshes (debug)} [unused if WrVTK=0] +False VTK_fields - Write mesh fields to VTK data files? (flag) {true/false} [unused if WrVTK=0] + 0 VTK_fps - Frame rate for VTK output (frames per second){will use closest integer multiple of DT} [used only if WrVTK=2 or WrVTK=3] diff --git a/example/MHK_RM1_Floating/MHK_RM1_Floating_AeroDyn.dat b/example/MHK_RM1_Floating/MHK_RM1_Floating_AeroDyn.dat new file mode 100644 index 00000000..f00e7f3e --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_Floating_AeroDyn.dat @@ -0,0 +1,145 @@ +------- AERODYN INPUT FILE -------------------------------------------------------------------------- +Floating MHK turbine hydrodynamic input properties, based on the RM1 tidal current rotor +====== General Options ============================================================================ +False Echo - Echo the input to ".AD.ech"? (flag) +"default" DTAero - Time interval for aerodynamic calculations {or "default"} (s) +1 Wake_Mod - Wake/induction model (switch) {0=none, 1=BEMT, 3=OLAF} [Wake_Mod cannot be 2 or 3 when linearizing] +1 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction} +0 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model} +True TwrAero - Calculate tower aerodynamic loads? (flag) +True CavitCheck - Perform cavitation check? (flag) [UA_Mod must be 0 when CavitCheck=true] +True Buoyancy - Include buoyancy effects? (flag) +False NacelleDrag - Include Nacelle Drag effects? (flag) +False CompAA - Flag to compute AeroAcoustics calculation [used only when Wake_Mod = 1 or 2] +"unused" AA_InputFile - AeroAcoustics input file [used only when CompAA=true] +====== Environmental Conditions =================================================================== +"default" AirDens - Air density (kg/m^3) +"default" KinVisc - Kinematic viscosity of working fluid (m^2/s) +"default" SpdSound - Speed of sound in working fluid (m/s) +"default" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True] +"default" Pvap - Vapour pressure of working fluid (Pa) [used only when CavitCheck=True] +====== Blade-Element/Momentum Theory Options ====================================================== [unused when Wake_Mod=0 or 3, except for BEM_Mod] +1 BEM_Mod - BEM model {1=legacy NoSweepPitchTwist, 2=polar} (switch) [used for all Wake_Mod to determine output coordinate system] +--- Skew correction +1 Skew_Mod - Skew model {0=No skew model, -1=Remove non-normal component for linearization, 1=skew model active} +False SkewMomCorr - Turn the skew momentum correction on or off [used only when Skew_Mod=1] +default SkewRedistr_Mod - Type of skewed-wake correction model (switch) {0=no redistribution, 1=Glauert/Pitt/Peters, default=1} [used only when Skew_Mod=1] +"default" SkewRedistrFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when Skew_Mod=1 and SkewRedistr_Mod=1] +--- BEM algorithm +True TipLoss - Use the Prandtl tip-loss model? (flag) [unused when Wake_Mod=0 or 3] +True HubLoss - Use the Prandtl hub-loss model? (flag) [unused when Wake_Mod=0 or 3] +True TanInd - Include tangential induction in BEMT calculations? (flag) [unused when Wake_Mod=0 or 3] +True AIDrag - Include the drag term in the axial-induction calculation? (flag) [unused when Wake_Mod=0 or 3] +True TIDrag - Include the drag term in the tangential-induction calculation? (flag) [unused when Wake_Mod=0,3 or TanInd=FALSE] +"default" IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when Wake_Mod=0 or 3] +1000 MaxIter - Maximum number of iteration steps (-) [unused when Wake_Mod=0] +--- Shear correction +False SectAvg - Use sector averaging (flag) +1 SectAvgWeighting - Weighting function for sector average {1=Uniform, default=1} within a sector centered on the blade (switch) [used only when SectAvg=True] +default SectAvgNPoints - Number of points per sectors (-) {default=5} [used only when SectAvg=True] +default SectAvgPsiBwd - Backward azimuth relative to blade where the sector starts (<=0) {default=-60} (deg) [used only when SectAvg=True] +default SectAvgPsiFwd - Forward azimuth relative to blade where the sector ends (>=0) {default=60} (deg) [used only when SectAvg=True] +--- Dynamic wake/inflow +2 DBEMT_Mod - Type of dynamic BEMT (DBEMT) model {0=No Dynamic Wake, -1=Frozen Wake for linearization, 1:constant tau1, 2=time-dependent tau1, 3=constant tau1 with continuous formulation} (-) +4 tau1_const - Time constant for DBEMT (s) [used only when DBEMT_Mod=1 or 3] +====== OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options ================== [used only when Wake_Mod=3] +"unused" OLAFInputFileName - Input file for OLAF [used only when Wake_Mod=3] +====== Unsteady Airfoil Aerodynamics Options ==================================================== +False AoA34 - Sample the angle of attack (AoA) at the 3/4 chord or the AC point {default=True} [always used] +0 UA_Mod - Unsteady Aero Model Switch (switch) {0=Quasi-steady (no UA), 2=B-L Gonzalez, 3=B-L Minnema/Pierce, 4=B-L HGM 4-states, 5=B-L HGM+vortex 5 states, 6=Oye, 7=Boeing-Vertol} +True FLookup - Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when UA_Mod>0] +3 IntegrationMethod - Switch to indicate which integration method UA uses (1=RK4, 2=AB4, 3=ABM4, 4=BDF2) +0 UAStartRad - Starting radius for dynamic stall (fraction of rotor radius [0.0,1.0]) [used only when UA_Mod>0; if line is missing UAStartRad=0] +1 UAEndRad - Ending radius for dynamic stall (fraction of rotor radius [0.0,1.0]) [used only when UA_Mod>0; if line is missing UAEndRad=1] +====== Airfoil Information ========================================================================= +2 AFTabMod - Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-) +1 InCol_Alfa - The column in the airfoil tables that contains the angle of attack (-) +2 InCol_Cl - The column in the airfoil tables that contains the lift coefficient (-) +3 InCol_Cd - The column in the airfoil tables that contains the drag coefficient (-) +0 InCol_Cm - The column in the airfoil tables that contains the pitching-moment coefficient; use zero if there is no Cm column (-) +4 InCol_Cpmin - The column in the airfoil tables that contains the Cpmin coefficient; use zero if there is no Cpmin column (-) +9 NumAFfiles - Number of airfoil files used (-) +"Airfoils/NACA6_1000.dat" AFNames - Airfoil file names (NumAFfiles lines) (quoted strings) +"Airfoils/NACA6_0864.dat" +"Airfoils/NACA6_0629.dat" +"Airfoils/NACA6_0444.dat" +"Airfoils/NACA6_0329.dat" +"Airfoils/NACA6_0276.dat" +"Airfoils/NACA6_0259.dat" +"Airfoils/NACA6_0247.dat" +"Airfoils/NACA6_0240.dat" +====== Rotor/Blade Properties ===================================================================== +False UseBlCm - Include aerodynamic pitching moment in calculations? (flag) +"MHK_RM1_AeroDyn_Blade.dat" ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (-) +"MHK_RM1_AeroDyn_Blade.dat" ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl < 2] +"unused" ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 (-) [unused if NumBl < 3] +====== Hub Properties ============================================================================== [used only when Buoyancy=True] +7.2 VolHub - Hub volume (m^3) +0.2222 HubCenBx - Hub center of buoyancy x direction offset (m) +====== Nacelle Properties ========================================================================== [used only when Buoyancy=True or NacelleDrag=True] +38.6 VolNac - Nacelle volume (m^3) +0.43, 0, 0 NacCenB - Position of nacelle center of buoyancy from yaw bearing in nacelle coordinates (m) +0, 0, 0 NacArea - Projected area of the nacelle in X, Y, Z in the nacelle coordinate system (m^2) +0, 0, 0 NacCd - Drag coefficient for the nacelle areas defined above (-) +0, 0, 0 NacDragAC - Position of aerodynamic center of nacelle drag in nacelle coordinates (m) +====== Tail Fin Aerodynamics ======================================================================= +False TFinAero - Calculate tail fin aerodynamics model (flag) +"unused" TFinFile - Input file for tail fin aerodynamics [used only when TFinAero=True] +====== Tower Influence and Aerodynamics ============================================================ [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] +4 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] +TwrElev TwrDiam TwrCd TwrTI TwrCb ! TwrTI used only when TwrShadow=2; TwrCb used only when Buoyancy=True +(m) (m) (-) (-) (-) +-9.0000000E+00 3.2530000E-01 2.0000000E-01 0.0000000E+00 1.0000000E+00 +-1.4000000E+01 3.2530000E-01 2.0000000E-01 0.0000000E+00 1.0000000E+00 +-1.9000000E+01 3.2530000E-01 2.0000000E-01 0.0000000E+00 1.0000000E+00 +-2.4000000E+01 3.2530000E-01 2.0000000E-01 0.0000000E+00 1.0000000E+00 +====== Outputs ==================================================================================== +True SumPrint - Generate a summary file listing input options and interpolated properties to ".AD.sum"? (flag) +9 NBlOuts - Number of blade node outputs [0 - 9] (-) +1, 5, 9, 13, 17, 21, 25, 27, 30 BlOutNd - Blade nodes whose values will be output (-) +4 NTwOuts - Number of tower node outputs [0 - 9] (-) +1, 2, 3, 4 TwOutNd - Tower nodes whose values will be output (-) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"TwN1Fbx" - x-component of buoyant force per unit length at Tw node 1 +"TwN3Fby" - y-component of buoyant force per unit length at Tw node 3 +"TwN4Fbz" - z-component of buoyant force per unit length at Tw node 4 +"TwN1Mbx" - x-component of buoyant moment per unit length at Tw node 6 +"TwN2Mby" - y-component of buoyant moment per unit length at Tw node 5 +"TwN3Mbz" - z-component of buoyant moment per unit length at Tw node 2 +"B2N4Fbn" - Buoyant force normal to chord per unit length at blade 2 node 4 +"B1N7Fbt" - Buoyant force tangential to chord per unit length at blade 1 node 7 +"B2N8Fbs" - Buoyant spanwise force per unit length at blade 2 node 8 +"B1N2Mbn" - Buoyant moment normal to chord per unit length at blade 1 node 2 +"B2N3Mbt" - Buoyant moment tangential to chord per unit length at blade 2 node 3 +"B1N6Mbs" - Buoyant spanwise moment per unit length at blade 1 node 6 +"B1FldFz" - Total blade aerodynamic/hydrodynamic load for blade 1 (force in z-direction) +"B2FldMx" - Total blade aerodynamic/hydrodynamic load for blade 2 (moment in x-direction) +"HbFbx" - x-component of buoyant force at hub node +"HbFby" - y-component of buoyant force at hub node +"HbFbz" - z-component of buoyant force at hub node +"HbMbx" - x-component of buoyant moment at hub node +"HbMby" - y-component of buoyant moment at hub node +"HbMbz" - z-component of buoyant moment at hub node +"NcFbx" - x-component of buoyant force at nacelle node +"NcFby" - y-component of buoyant force at nacelle node +"NcFbz" - z-component of buoyant force at nacelle node +"NcMbx" - x-component of buoyant moment at nacelle node +"NcMby" - y-component of buoyant moment at nacelle node +"NcMbz" - z-component of buoyant moment at nacelle node +"RtFldFxh" - Total rotor aerodynamic/hydrodynamic and buoyant load (force in x direction) +"RtFldFyh" - Total rotor aerodynamic/hydrodynamic and buoyant load (force in y direction) +"RtFldFzg" - Total rotor aerodynamic/hydrodynamic and buoyant load (force in global z direction) +"RtFldMxh" - Total rotor aerodynamic/hydrodynamic and buoyant load (moment in x direction) +"RtFldMyg" - Total rotor aerodynamic/hydrodynamic and buoyant load (moment in global y direction) +"RtFldMzh" - Total rotor aerodynamic/hydrodynamic and buoyant load (moment in z direction) +"B1N3SigCr" - Critical cavitation number blade 1 node 3 +"B2N5SigCr" - Critical cavitation number blade 2 node 5 +"B1N2SgCav" - Cavitation number blade 1 node 2 +"B2N6SgCav" - Cavitation number blade 2 node 6 +END of OutList section (the word "END" must appear in the first 3 columns of the last OutList line) +---------------------- NODE OUTPUTS -------------------------------------------- +1 BldNd_BladesOut - Number of blades to output all node information at. Up to number of blades on turbine. (-) +ALL BldNd_BlOutNd - Specify a portion of the nodes to output. {"ALL", "Tip", "Root", or a list of node numbers} (-) + OutList_Nodal - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +END (the word "END" must appear in the first 3 columns of this last OutList line in the optional nodal output section) +==================================================================================================== diff --git a/example/MHK_RM1_Floating/MHK_RM1_Floating_ElastoDyn.dat b/example/MHK_RM1_Floating/MHK_RM1_Floating_ElastoDyn.dat new file mode 100644 index 00000000..d1a38617 --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_Floating_ElastoDyn.dat @@ -0,0 +1,152 @@ +------- ELASTODYN for OpenFAST INPUT FILE ------------------------------------------- +Floating MHK turbine structural input properties, based on the RM1 tidal current rotor +---------------------- SIMULATION CONTROL -------------------------------------- +False Echo - Echo input data to ".ech" (flag) + 3 Method - Integration method: {1: RK4, 2: AB4, or 3: ABM4} (-) +"default" DT - Integration time step (s) +---------------------- DEGREES OF FREEDOM -------------------------------------- +False FlapDOF1 - First flapwise blade mode DOF (flag) +False FlapDOF2 - Second flapwise blade mode DOF (flag) +False EdgeDOF - First edgewise blade mode DOF (flag) +False TeetDOF - Rotor-teeter DOF (flag) [unused for 3 blades] +False DrTrDOF - Drivetrain rotational-flexibility DOF (flag) +False GenDOF - Generator DOF (flag) +False YawDOF - Yaw DOF (flag) +False TwFADOF1 - First fore-aft tower bending-mode DOF (flag) +False TwFADOF2 - Second fore-aft tower bending-mode DOF (flag) +False TwSSDOF1 - First side-to-side tower bending-mode DOF (flag) +False TwSSDOF2 - Second side-to-side tower bending-mode DOF (flag) +True PtfmSgDOF - Platform horizontal surge translation DOF (flag) +True PtfmSwDOF - Platform horizontal sway translation DOF (flag) +True PtfmHvDOF - Platform vertical heave translation DOF (flag) +True PtfmRDOF - Platform roll tilt rotation DOF (flag) +True PtfmPDOF - Platform pitch tilt rotation DOF (flag) +True PtfmYDOF - Platform yaw rotation DOF (flag) +---------------------- INITIAL CONDITIONS -------------------------------------- + 0 OoPDefl - Initial out-of-plane blade-tip displacement (meters) + 0 IPDefl - Initial in-plane blade-tip deflection (meters) + 0 BlPitch(1) - Blade 1 initial pitch (degrees) + 0 BlPitch(2) - Blade 2 initial pitch (degrees) + 0 BlPitch(3) - Blade 3 initial pitch (degrees) [unused for 2 blades] + 0 TeetDefl - Initial or fixed teeter angle (degrees) [unused for 3 blades] + 0 Azimuth - Initial azimuth angle for blade 1 (degrees) + 11.5 RotSpeed - Initial or fixed rotor speed (rpm) + 0 NacYaw - Initial or fixed nacelle-yaw angle (degrees) + 0 TTDspFA - Initial fore-aft tower-top displacement (meters) + 0 TTDspSS - Initial side-to-side tower-top displacement (meters) + 20 PtfmSurge - Initial or fixed horizontal surge translational displacement of platform (meters) + 0 PtfmSway - Initial or fixed horizontal sway translational displacement of platform (meters) + 0 PtfmHeave - Initial or fixed vertical heave translational displacement of platform (meters) + 0 PtfmRoll - Initial or fixed roll tilt rotational displacement of platform (degrees) + 0 PtfmPitch - Initial or fixed pitch tilt rotational displacement of platform (degrees) + 0 PtfmYaw - Initial or fixed yaw rotational displacement of platform (degrees) +---------------------- TURBINE CONFIGURATION ----------------------------------- + 2 NumBl - Number of blades (-) + 10 TipRad - The distance from the rotor apex to the blade tip (meters) + 1 HubRad - The distance from the rotor apex to the blade root (meters) + 0 PreCone(1) - Blade 1 cone angle (degrees) + 0 PreCone(2) - Blade 2 cone angle (degrees) + 0 PreCone(3) - Blade 3 cone angle (degrees) [unused for 2 blades] + 0.2222 HubCM - Distance from rotor apex to hub mass [positive downwind] (meters) + 0 UndSling - Undersling length [distance from teeter pin to the rotor apex] (meters) [unused for 3 blades] + 0 Delta3 - Delta-3 angle for teetering rotors (degrees) [unused for 3 blades] + 0 AzimB1Up - Azimuth value to use for I/O when blade 1 points up (degrees) + -4.91 OverHang - Distance from yaw axis to rotor apex [3 blades] or teeter pin [2 blades] (meters) + 0 ShftGagL - Distance from rotor apex [3 blades] or teeter pin [2 blades] to shaft strain gages [positive for upwind rotors] (meters) + 0 ShftTilt - Rotor shaft tilt angle (degrees) + 0.43 NacCMxn - Downwind distance from the tower-top to the nacelle CM (meters) + 0 NacCMyn - Lateral distance from the tower-top to the nacelle CM (meters) + -1.2 NacCMzn - Vertical distance from the tower-top to the nacelle CM (meters) + 0 NcIMUxn - Downwind distance from the tower-top to the nacelle IMU (meters) + 0 NcIMUyn - Lateral distance from the tower-top to the nacelle IMU (meters) + -1.2 NcIMUzn - Vertical distance from the tower-top to the nacelle IMU (meters) + -1.2 Twr2Shft - Vertical distance from the tower-top to the rotor shaft (meters) + -24 TowerHt - Height of tower relative to ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] (meters) + -9 TowerBsHt - Height of tower base relative to ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] (meters) + 0 PtfmCMxt - Downwind distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters) + 0 PtfmCMyt - Lateral distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters) + -6.09 PtfmCMzt - Vertical distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters) + 0 PtfmRefzt - Vertical distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform reference point (meters) +---------------------- MASS AND INERTIA ---------------------------------------- + 0 TipMass(1) - Tip-brake mass, blade 1 (kg) + 0 TipMass(2) - Tip-brake mass, blade 2 (kg) + 0 TipMass(3) - Tip-brake mass, blade 3 (kg) [unused for 2 blades] + 140 HubMass - Hub mass (kg) + 79.6 HubIner - Hub inertia about rotor axis [3 blades] or teeter axis [2 blades] (kg m^2) + 139.5 GenIner - Generator inertia about HSS (kg m^2) + 40100 NacMass - Nacelle mass (kg) + 244643 NacYIner - Nacelle inertia about yaw axis (kg m^2) + 0 YawBrMass - Yaw bearing mass (kg) + 2525214 PtfmMass - Platform mass (kg) + 195242474 PtfmRIner - Platform inertia for roll tilt rotation about the platform CM (kg m^2) + 919435755 PtfmPIner - Platform inertia for pitch tilt rotation about the platform CM (kg m^2) + 1053535885 PtfmYIner - Platform inertia for yaw rotation about the platform CM (kg m^2) + 0 PtfmXYIner - Platform xy moment of inertia about the platform CM (=-int(xydm)) (kg m^2) + 0 PtfmYZIner - Platform yz moment of inertia about the platform CM (=-int(yzdm)) (kg m^2) + 0 PtfmXZIner - Platform xz moment of inertia about the platform CM (=-int(xzdm)) (kg m^2) +---------------------- BLADE --------------------------------------------------- + 8 BldNodes - Number of blade nodes (per blade) used for analysis (-) +"MHK_RM1_ElastoDyn_Blade.dat" BldFile(1) - Name of file containing properties for blade 1 (quoted string) +"MHK_RM1_ElastoDyn_Blade.dat" BldFile(2) - Name of file containing properties for blade 2 (quoted string) +"unused" BldFile(3) - Name of file containing properties for blade 3 (quoted string) [unused for 2 blades] +---------------------- ROTOR-TEETER -------------------------------------------- + 0 TeetMod - Rotor-teeter spring/damper model {0: none, 1: standard, 2: user-defined from routine UserTeet} (switch) [unused for 3 blades] + 0 TeetDmpP - Rotor-teeter damper position (degrees) [used only for 2 blades and when TeetMod=1] + 0 TeetDmp - Rotor-teeter damping constant (N-m/(rad/s)) [used only for 2 blades and when TeetMod=1] + 0 TeetCDmp - Rotor-teeter rate-independent Coulomb-damping moment (N-m) [used only for 2 blades and when TeetMod=1] + 0 TeetSStP - Rotor-teeter soft-stop position (degrees) [used only for 2 blades and when TeetMod=1] + 0 TeetHStP - Rotor-teeter hard-stop position (degrees) [used only for 2 blades and when TeetMod=1] + 0 TeetSSSp - Rotor-teeter soft-stop linear-spring constant (N-m/rad) [used only for 2 blades and when TeetMod=1] + 0 TeetHSSp - Rotor-teeter hard-stop linear-spring constant (N-m/rad) [used only for 2 blades and when TeetMod=1] +---------------------- YAW-FRICTION -------------------------------------------- + 0 YawFrctMod - Yaw-friction model {0: none, 1: friction independent of yaw-bearing force and bending moment, 2: friction with Coulomb terms depending on yaw-bearing force and bending moment, 3: user defined model} (switch) + 300 M_CSmax - Maximum static Coulomb friction torque (N-m) [M_CSmax when YawFrctMod=1; |Fz|*M_CSmax when YawFrctMod=2 and Fz<0] + 0 M_FCSmax - Maximum static Coulomb friction torque proportional to yaw bearing shear force (N-m) [sqrt(Fx^2+Fy^2)*M_FCSmax; only used when YawFrctMod=2] + 0 M_MCSmax - Maximum static Coulomb friction torque proportional to yaw bearing bending moment (N-m) [sqrt(Mx^2+My^2)*M_MCSmax; only used when YawFrctMod=2] + 40 M_CD - Dynamic Coulomb friction moment (N-m) [M_CD when YawFrctMod=1; |Fz|*M_CD when YawFrctMod=2 and Fz<0] + 0 M_FCD - Dynamic Coulomb friction moment proportional to yaw bearing shear force (N-m) [sqrt(Fx^2+Fy^2)*M_FCD; only used when YawFrctMod=2] + 0 M_MCD - Dynamic Coulomb friction moment proportional to yaw bearing bending moment (N-m) [sqrt(Mx^2+My^2)*M_MCD; only used when YawFrctMod=2] + 0 sig_v - Linear viscous friction coefficient (N-m/(rad/s)) + 0 sig_v2 - Quadratic viscous friction coefficient (N-m/(rad/s)^2) + 0 OmgCut - Yaw angular velocity cutoff below which viscous friction is linearized (rad/s) +---------------------- DRIVETRAIN ---------------------------------------------- + 92 GBoxEff - Gearbox efficiency (%) + 53 GBRatio - Gearbox ratio (-) + 600000 DTTorSpr - Drivetrain torsional spring (N-m/rad) + 100000 DTTorDmp - Drivetrain torsional damper (N-m/(rad/s)) +---------------------- FURLING ------------------------------------------------- +False Furling - Read in additional model properties for furling turbine (flag) [must currently be FALSE) +"unused" FurlFile - Name of file containing furling properties (quoted string) [unused when Furling=False] +---------------------- TOWER --------------------------------------------------- + 2 TwrNodes - Number of tower nodes used for analysis (-) +"MHK_RM1_Floating_ElastoDyn_Tower.dat" TwrFile - Name of file containing tower properties (quoted string) +---------------------- OUTPUT -------------------------------------------------- +True SumPrint - Print summary data to ".sum" (flag) + 1 OutFile - Switch to determine where output will be placed: {1: in module output file only; 2: in glue code output file only; 3: both} (currently unused) +True TabDelim - Use tab delimiters in text tabular output file? (flag) (currently unused) +"ES10.3E2" OutFmt - Format used for text tabular output (except time). Resulting field should be 10 characters. (quoted string) (currently unused) + 0 TStart - Time to begin tabular output (s) (currently unused) + 1 DecFact - Decimation factor for tabular output {1: output every time step} (-) (currently unused) + 0 NTwGages - Number of tower nodes that have strain gages for output [0 to 9] (-) + 0 TwrGagNd - List of tower nodes that have strain gages [1 to TwrNodes] (-) [unused if NTwGages=0] + 0 NBlGages - Number of blade nodes that have strain gages for output [0 to 9] (-) + 0 BldGagNd - List of blade nodes that have strain gages [1 to BldNodes] (-) [unused if NBlGages=0] + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"PtfmSurge" +"PtfmSway" +"PtfmHeave" +"PtfmRoll" +"PtfmPitch" +"PtfmYaw" +"TwrTpTDxi" +"TwrTpTDyi" +"TwrTpTDzi" +"OoPDefl1" +END of OutList section (the word "END" must appear in the first 3 columns of the last OutList line) +====== Outputs for all blade stations (same ending as above for Spn1.... =========================== [optional section] + 1 BldNd_BladesOut - Number of blades to output all node information at. Up to number of blades on turbine. (-) +"All" BldNd_BlOutNd - Future feature will allow selecting a portion of the nodes to output. Not implemented yet. (-) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +END (the word "END" must appear in the first 3 columns of this last OutList line in the optional nodal output section) +---------------------------------------------------------------- + diff --git a/example/MHK_RM1_Floating/MHK_RM1_Floating_ElastoDyn_Tower.dat b/example/MHK_RM1_Floating/MHK_RM1_Floating_ElastoDyn_Tower.dat new file mode 100644 index 00000000..f54dee11 --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_Floating_ElastoDyn_Tower.dat @@ -0,0 +1,46 @@ + ------- ELASTODYN V1.00.* TOWER INPUT FILE ------------------------------------- +Floating MHK turbine structural tower input properties, based on the RM1 tidal current rotor +---------------------- TOWER PARAMETERS ---------------------------------------- + 5 NTwInpSt - Number of input stations to specify tower geometry + 1 TwrFADmp(1) - Tower 1st fore-aft mode structural damping ratio (%) + 1 TwrFADmp(2) - Tower 2nd fore-aft mode structural damping ratio (%) + 1 TwrSSDmp(1) - Tower 1st side-to-side mode structural damping ratio (%) + 1 TwrSSDmp(2) - Tower 2nd side-to-side mode structural damping ratio (%) +---------------------- TOWER ADJUSTMUNT FACTORS -------------------------------- + 1 FAStTunr(1) - Tower fore-aft modal stiffness tuner, 1st mode (-) + 1 FAStTunr(2) - Tower fore-aft modal stiffness tuner, 2nd mode (-) + 1 SSStTunr(1) - Tower side-to-side stiffness tuner, 1st mode (-) + 1 SSStTunr(2) - Tower side-to-side stiffness tuner, 2nd mode (-) + 1 AdjTwMa - Factor to adjust tower mass density (-) + 1 AdjFASt - Factor to adjust tower fore-aft stiffness (-) + 1 AdjSSSt - Factor to adjust tower side-to-side stiffness (-) +---------------------- DISTRIBUTED TOWER PROPERTIES ---------------------------- +HtFract TMassDen TwFAStif TwSSStif +(-) (kg/m) (Nm^2) (Nm^2) +0.00 652.34 5.62E+09 5.66E+08 +0.25 652.34 5.62E+09 5.66E+08 +0.50 652.34 5.62E+09 5.66E+08 +0.75 652.34 5.62E+09 5.66E+08 +1.00 652.34 5.62E+09 5.66E+08 +---------------------- TOWER FORE-AFT MODE SHAPES ------------------------------ + 1.4869000 TwFAM1Sh(2) - Mode 1, coefficient of x^2 term + -0.4901000 TwFAM1Sh(3) - , coefficient of x^3 term + 0.0024004 TwFAM1Sh(4) - , coefficient of x^4 term + -0.0014264 TwFAM1Sh(5) - , coefficient of x^5 term + 0.0022151 TwFAM1Sh(6) - , coefficient of x^6 term + 47.3126000 TwFAM2Sh(2) - Mode 2, coefficient of x^2 term + -47.0099000 TwFAM2Sh(3) - , coefficient of x^3 term + -6.1018000 TwFAM2Sh(4) - , coefficient of x^4 term + 8.9324000 TwFAM2Sh(5) - , coefficient of x^5 term + -2.1333000 TwFAM2Sh(6) - , coefficient of x^6 term +---------------------- TOWER SIDE-TO-SIDE MODE SHAPES -------------------------- + 1.5007000 TwSSM1Sh(2) - Mode 1, coefficient of x^2 term + -0.4979700 TwSSM1Sh(3) - , coefficient of x^3 term + -0.0116500 TwSSM1Sh(4) - , coefficient of x^4 term + 0.0104020 TwSSM1Sh(5) - , coefficient of x^5 term + -0.0014532 TwSSM1Sh(6) - , coefficient of x^6 term + 408.3002000 TwSSM2Sh(2) - Mode 2, coefficient of x^2 term +-420.2848000 TwSSM2Sh(3) - , coefficient of x^3 term +-111.0241000 TwSSM2Sh(4) - , coefficient of x^4 term + 166.6788000 TwSSM2Sh(5) - , coefficient of x^5 term + -42.6701000 TwSSM2Sh(6) - , coefficient of x^6 term \ No newline at end of file diff --git a/example/MHK_RM1_Floating/MHK_RM1_Floating_HydroDyn.dat b/example/MHK_RM1_Floating/MHK_RM1_Floating_HydroDyn.dat new file mode 100644 index 00000000..e60b6684 --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_Floating_HydroDyn.dat @@ -0,0 +1,173 @@ +------- HydroDyn Input File ---------------------------------------------------- +Floating MHK turbine hydrodynamic support structure input properties, based on the RM1 tidal current rotor with a quad-style floating platform +False Echo - Echo the input file data (flag) +---------------------- FLOATING PLATFORM --------------------------------------- [unused with WaveMod=6] + 1 PotMod - Potential-flow model {0: none=no potential flow, 1: frequency-to-time-domain transforms based on WAMIT output, 2: fluid-impulse theory (FIT)} (switch) + 1 ExctnMod - Wave-excitation model {0: no wave-excitation calculation, 1: DFT, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ssexctn INPUT FILE] + 0 ExctnDisp - Method of computing Wave Excitation {0: use undisplaced position, 1: use displaced position, 2: use low-pass filtered displaced position) [only used when PotMod=1 and ExctnMod>0 and SeaState's WaveMod>0]} (switch) + 0 ExctnCutOff - Cutoff (corner) frequency of the low-pass time-filtered displaced position (Hz) [>0.0] [used only when PotMod=1, ExctnMod>0, and ExctnDisp=2]) [only used when PotMod=1 and ExctnMod>0 and SeaState's WaveMod>0]} (switch) + 0 PtfmYMod - Model for large platform yaw offset {0: Static reference yaw offset based on PtfmRefY, 1: dynamic reference yaw offset based on low-pass filtering the PRP yaw motion with cutoff frequency PtfmYCutOff} (switch) + 0 PtfmRefY - Constant (if PtfmYMod=0) or initial (if PtfmYMod=1) platform reference yaw offset (deg) + 0.01 PtfmYCutOff - Cutoff frequency for the low-pass filtering of PRP yaw motion when PtfmYMod=1 [unused when PtfmYMod=0] (Hz) + 36 NExctnHdg - Number of evenly distributed platform yaw/heading angles over the range of [-180, 180) deg for which the wave excitation shall be computed [only used when PtfmYMod=1] (-) + 1 RdtnMod - Radiation memory-effect model {0: no memory-effect calculation, 1: convolution, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ss INPUT FILE] + 60 RdtnTMax - Analysis time for wave radiation kernel calculations (sec) [only used when PotMod=1 and RdtnMod>0; determines RdtnDOmega=Pi/RdtnTMax in the cosine transform; MAKE SURE THIS IS LONG ENOUGH FOR THE RADIATION IMPULSE RESPONSE FUNCTIONS TO DECAY TO NEAR-ZERO FOR THE GIVEN PLATFORM!] + "DEFAULT" RdtnDT - Time step for wave radiation kernel calculations (sec) [only used when PotMod=1 and ExctnMod>0 or RdtnMod>0; DT<=RdtnDT<=0.1 recommended; determines RdtnOmegaMax=Pi/RdtnDT in the cosine transform] + 1 NBody - Number of WAMIT bodies to be used (-) [>=1; only used when PotMod=1. If NBodyMod=1, the WAMIT data contains a vector of size 6*NBody x 1 and matrices of size 6*NBody x 6*NBody; if NBodyMod>1, there are NBody sets of WAMIT data each with a vector of size 6 x 1 and matrices of size 6 x 6] + 2 NBodyMod - Body coupling model {1: include coupling terms between each body and NBody in HydroDyn equals NBODY in WAMIT, 2: neglect coupling terms between each body and NBODY=1 with XBODY=0 in WAMIT, 3: Neglect coupling terms between each body and NBODY=1 with XBODY=/0 in WAMIT} (switch) [only used when PotMod=1] +"MHK_RM1_Floating" PotFile - Root name of potential-flow model data; WAMIT output files containing the linear, nondimensionalized, hydrostatic restoring matrix (.hst), frequency-dependent hydrodynamic added mass matrix and damping matrix (.1), and frequency- and direction-dependent wave excitation force vector per unit wave amplitude (.3) (quoted string) [1 to NBody if NBodyMod>1] [MAKE SURE THE FREQUENCIES INHERENT IN THESE WAMIT FILES SPAN THE PHYSICALLY-SIGNIFICANT RANGE OF FREQUENCIES FOR THE GIVEN PLATFORM; THEY MUST CONTAIN THE ZERO- AND INFINITE-FREQUENCY LIMITS!] + 1 WAMITULEN - Characteristic body length scale used to redimensionalize WAMIT output (meters) [1 to NBody if NBodyMod>1] [only used when PotMod=1] + 0 PtfmRefxt - The xt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1] + 0 PtfmRefyt - The yt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1] + 0 PtfmRefzt - The zt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1. If NBodyMod=2,PtfmRefzt=0.0] + 0 PtfmRefztRot - The rotation about zt of the body reference frame(s) from xt/yt (degrees) [1 to NBody] [only used when PotMod=1] + 2671.85 PtfmVol0 - Displaced volume of water when the body is in its undisplaced position (m^3) [1 to NBody] [only used when PotMod=1; USE THE SAME VALUE COMPUTED BY WAMIT AS OUTPUT IN THE .OUT FILE!] + 0 PtfmCOBxt - The xt offset of the center of buoyancy (COB) from (0,0) (meters) [1 to NBody] [only used when PotMod=1] + 0 PtfmCOByt - The yt offset of the center of buoyancy (COB) from (0,0) (meters) [1 to NBody] [only used when PotMod=1] +---------------------- 2ND-ORDER FLOATING PLATFORM FORCES ---------------------- [unused with WaveMod=0 or 6, or PotMod=0 or 2] + 0 MnDrift - Mean-drift 2nd-order forces computed {0: None; [7, 8, 9, 10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero. If NBody>1, MnDrift /=8] + 0 NewmanApp - Mean- and slow-drift 2nd-order forces computed with Newman's approximation {0: None; [7, 8, 9, 10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero. If NBody>1, NewmanApp/=8. Used only when WaveDirMod=0] + 0 DiffQTF - Full difference-frequency 2nd-order forces computed with full QTF {0: None; [10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero] + 0 SumQTF - Full summation -frequency 2nd-order forces computed with full QTF {0: None; [10, 11, or 12]: WAMIT file to use} +---------------------- PLATFORM ADDITIONAL STIFFNESS AND DAMPING -------------- [unused with PotMod=0 or 2] + 0 AddF0 - Additional preload (N, N-m) [If NBodyMod=1, one size 6*NBody x 1 vector; if NBodyMod>1, NBody size 6 x 1 vectors] + 0 + 0 + 0 + 0 + 0 + 0 0 0 0 0 0 AddCLin - Additional linear stiffness (N/m, N/rad, N-m/m, N-m/rad) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod>1, NBody size 6 x 6 matrices] + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 AddBLin - Additional linear damping(N/(m/s), N/(rad/s), N-m/(m/s), N-m/(rad/s)) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod>1, NBody size 6 x 6 matrices] + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 AddBQuad - Additional quadratic drag(N/(m/s)^2, N/(rad/s)^2, N-m(m/s)^2, N-m/(rad/s)^2) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod>1, NBody size 6 x 6 matrices] + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 +---------------------- STRIP THEORY OPTIONS -------------------------------------- + 0 WaveDisp - Method of computing Wave Kinematics {0: use undisplaced position, 1: use displaced position) } (switch) + 0 AMMod - Method of computing distributed added-mass force. (0: Only and always on nodes below SWL at the undisplaced position. 2: Up to the instantaneous free surface) [overwrite to 0 when WaveMod = 0 or 6 or when WaveStMod = 0 in SeaState] +---------------------- AXIAL COEFFICIENTS -------------------------------------- + 2 NAxCoef - Number of axial coefficients (-) +AxCoefID AxCd AxCa AxCp AxFDMod AxVnCOff AxFDLoFSc + (-) (-) (-) (-) (-) (-) (-) + 1 0.00 0.00 0.00 0 -1.00 1.00 ! Columns / Braces (no exposed member ends) + 2 1.00 1.00 1.00 0 -1.00 1.00 ! Heave Plates +---------------------- MEMBER JOINTS ------------------------------------------- + 33 NJoints - Number of joints (-) [must be exactly 0 or at least 2] +JointID Jointxi Jointyi Jointzi JointAxID JointOvrlp [JointOvrlp= 0: do nothing at joint, 1: eliminate overlaps by calculating super member] + (-) (m) (m) (m) (-) (switch) + 0 28.00000 0.00000 -10.00000 1 0 ! Downstream Column + 1 28.00000 0.00000 6.00000 1 0 + 2 -28.00000 0.00000 -10.00000 1 0 ! Upstream Column + 3 -28.00000 0.00000 6.00000 1 0 + 4 0.00000 -12.00000 -10.00000 1 0 ! Starboard Column + 5 0.00000 -12.00000 6.00000 1 0 + 6 0.00000 12.00000 -10.00000 1 0 ! Port Column + 7 0.00000 12.00000 6.00000 1 0 + 8 3.67658 10.42430 4.50000 1 0 ! Upper Braces + 9 24.32340 1.57568 4.50000 1 0 + 10 3.67658 -10.42430 4.50000 1 0 + 11 24.32340 -1.57568 4.50000 1 0 + 12 -3.67658 10.42430 4.50000 1 0 + 13 -24.32340 1.57568 4.50000 1 0 + 14 -3.67658 -10.42430 4.50000 1 0 + 15 -24.32340 -1.57568 4.50000 1 0 + 16 3.67658 10.42430 -8.50000 1 0 ! Lower Braces + 17 24.32340 1.57568 -8.50000 1 0 + 18 3.67658 -10.42430 -8.50000 1 0 + 19 24.32340 -1.57568 -8.50000 1 0 + 20 -3.67658 10.42430 -8.50000 1 0 + 21 -24.32340 1.57568 -8.50000 1 0 + 22 -3.67658 -10.42430 -8.50000 1 0 + 23 -24.32340 -1.57568 -8.50000 1 0 + 24 0.00000 -8.00000 4.50000 1 0 ! Tower Braces + 25 0.00000 8.00000 4.50000 1 0 + 26 0.00000 -8.00000 -8.50000 1 0 + 27 0.00000 8.00000 -8.50000 1 0 + 28 0.00000 0.00000 -8.50000 1 0 + 29 28.00000 0.00000 -10.50000 2 0 ! Heave Plates + 30 -28.00000 0.00000 -10.50000 2 0 + 31 0.00000 -12.00000 -10.50000 2 0 + 32 0.00000 12.00000 -10.50000 2 0 +---------------------- MEMBER CROSS-SECTION PROPERTIES ------------------------- + 4 NPropSets - Number of member property sets (-) +PropSetID PropD PropThck + (-) (m) (m) + 0 8.00000 0.02000 ! Columns + 1 2.00000 0.02000 ! Braces + 2 2.00000 0.08100 ! Flooded Braces (not flooded in hydrodyn) + 3 12.00000 0.39250 ! Flooded Heave Plates (not flooded in hydrodyn) +---------------------- SIMPLE HYDRODYNAMIC COEFFICIENTS (model 1) -------------- + SimplCd SimplCdMG SimplCa SimplCaMG SimplCp SimplCpMG SimplAxCd SimplAxCdMG SimplAxCa SimplAxCaMG SimplAxCp SimplAxCpMG SimplCb SimplCbMG + (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) + 1.20 0.00 1.00 0.00 1.00 1.00 0.00 0.00 0.00 0.00 1.00 1.00 1.00 1.00 +---------------------- DEPTH-BASED HYDRODYNAMIC COEFFICIENTS (model 2) --------- + 0 NCoefDpth - Number of depth-dependent coefficients (-) +Dpth DpthCd DpthCdMG DpthCa DpthCaMG DpthCp DpthCpMG DpthAxCd DpthAxCdMG DpthAxCa DpthAxCaMG DpthAxCp DpthAxCpMG DpthCb DpthCbMG +(m) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) +---------------------- MEMBER-BASED HYDRODYNAMIC COEFFICIENTS (model 3) -------- + 0 NCoefMembers - Number of member-based coefficients (-) +MemberID MemberCd1 MemberCd2 MemberCdMG1 MemberCdMG2 MemberCa1 MemberCa2 MemberCaMG1 MemberCaMG2 MemberCp1 MemberCp2 MemberCpMG1 MemberCpMG2 MemberAxCd1 MemberAxCd2 MemberAxCdMG1 MemberAxCdMG2 MemberAxCa1 MemberAxCa2 MemberAxCaMG1 MemberAxCaMG2 MemberAxCp1 MemberAxCp2 MemberAxCpMG1 MemberAxCpMG2 MemberCb1 MemberCb2 MemberCbMG1 MemberCbMG2 + (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) +-------------------- MEMBERS ------------------------------------------------- + 20 NMembers - Number of members (-) +MemberID MJointID1 MJointID2 MPropSetID1 MPropSetID2 MDivSize MCoefMod MHstLMod PropPot [MCoefMod=1: use simple coeff table, 2: use depth-based coeff table, 3: use member-based coeff table] [ PropPot/=0 if member is modeled with potential-flow theory] + (-) (-) (-) (-) (-) (m) (switch) (switch) (flag) + 0 0 1 0 0 0.1000 1 1 TRUE ! Columns + 1 2 3 0 0 0.1000 1 1 TRUE + 2 4 5 0 0 0.1000 1 1 TRUE + 3 6 7 0 0 0.1000 1 1 TRUE + 4 8 9 1 1 0.1000 1 1 TRUE ! Upper Braces + 5 10 11 1 1 0.1000 1 1 TRUE + 6 12 13 1 1 0.1000 1 1 TRUE + 7 14 15 1 1 0.1000 1 1 TRUE + 8 16 17 2 2 0.1000 1 1 TRUE ! Lower Braces + 9 18 19 2 2 0.1000 1 1 TRUE + 10 20 21 2 2 0.1000 1 1 TRUE + 11 22 23 2 2 0.1000 1 1 TRUE + 12 24 25 1 1 0.1000 1 1 TRUE ! Tower Braces + 13 26 27 1 1 0.1000 1 1 TRUE + 14 24 28 1 1 0.1000 1 1 TRUE + 15 25 28 1 1 0.1000 1 1 TRUE + 16 0 29 3 3 0.1000 1 1 TRUE ! Heave Plates + 17 2 30 3 3 0.1000 1 1 TRUE + 18 4 31 3 3 0.1000 1 1 TRUE + 19 6 32 3 3 0.1000 1 1 TRUE +---------------------- FILLED MEMBERS ------------------------------------------ + 0 NFillGroups - Number of filled member groups (-) [If FillDens = DEFAULT, then FillDens = WtrDens; FillFSLoc is related to MSL2SWL] +FillNumM FillMList FillFSLoc FillDens +(-) (-) (m) (kg/m^3) +---------------------- MARINE GROWTH ------------------------------------------- + 0 NMGDepths - Number of marine-growth depths specified (-) +MGDpth MGThck MGDens +(m) (m) (kg/m^3) +---------------------- MEMBER OUTPUT LIST -------------------------------------- + 0 NMOutputs - Number of member outputs (-) [must be < 10] +MemberID NOutLoc NodeLocs [NOutLoc < 10; node locations are normalized distance from the start of the member, and must be >=0 and <= 1] [unused if NMOutputs=0] + (-) (-) (-) +---------------------- JOINT OUTPUT LIST --------------------------------------- + 0 NJOutputs - Number of joint outputs [Must be < 10] + 0 JOutLst - List of JointIDs which are to be output (-)[unused if NJOutputs=0] +---------------------- OUTPUT -------------------------------------------------- +True HDSum - Output a summary file [flag] +False OutAll - Output all user-specified member and joint loads (only at each member end, not interior locations) [flag] + 2 OutSwtch - Output requested channels to: [1=Hydrodyn.out, 2=GlueCode.out, 3=both files] +"E15.7e2" OutFmt - Output format for numerical results (quoted string) [not checked for validity!] +"A11" OutSFmt - Output format for header strings (quoted string) [not checked for validity!] +---------------------- OUTPUT CHANNELS ----------------------------------------- +Wave1Elev - Wave elevation at the platform reference point (0, 0) +HydroFxi - Buoyancy force [N] in the X direction. +HydroFyi - Buoyancy force [N] in the Y direction. +HydroFzi - Buoyancy force [N] in the vertical direction (Z). +END of output channels and end of file. (the word "END" must appear in the first 3 columns of this line) \ No newline at end of file diff --git a/example/MHK_RM1_Floating/MHK_RM1_Floating_InflowWind.dat b/example/MHK_RM1_Floating/MHK_RM1_Floating_InflowWind.dat new file mode 100644 index 00000000..a51d8ba7 --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_Floating_InflowWind.dat @@ -0,0 +1,68 @@ +------- InflowWind INPUT FILE ------------------------------------------------------------------------- +Steady 1.9 m/s inflow for floating MHK turbine, based on the RM1 tidal current rotor +--------------------------------------------------------------------------------------------------------------- +False Echo - Echo input data to .ech (flag) + 1 WindType - switch for wind file type (1=steady; 2=uniform; 3=binary TurbSim FF; 4=binary Bladed-style FF; 5=HAWC format; 6=User defined; 7=native Bladed FF) + 0 PropagationDir - Direction of wind propagation (meteorological rotation from aligned with X (positive rotates towards -Y) -- degrees) (not used for native Bladed format WindType=7) + 0 VFlowAng - Upflow angle (degrees) (not used for native Bladed format WindType=7) +False VelInterpCubic - Use cubic interpolation for velocity in time (false=linear, true=cubic) [Used with WindType=2,3,4,5,7] + 1 NWindVel - Number of points to output the wind velocity (0 to 9) + 0 WindVxiList - List of coordinates in the inertial X direction (m) + 0 WindVyiList - List of coordinates in the inertial Y direction (m) + 24.8 WindVziList - List of coordinates in the inertial Z direction (m) +================== Parameters for Steady Wind Conditions [used only for WindType = 1] ========================= + 1.9 HWindSpeed - Horizontal wind speed (m/s) + 24.8 RefHt - Reference height for horizontal wind speed (m) + 0.1429 PLExp - Power law exponent (-) +================== Parameters for Uniform wind file [used only for WindType = 2] ============================ +"unused" FileName_Uni - Filename of time series data for uniform wind field. (-) + 30 RefHt_Uni - Reference height for horizontal wind speed (m) + 125.88 RefLength - Reference length for linear horizontal and vertical sheer (-) +================== Parameters for Binary TurbSim Full-Field files [used only for WindType = 3] ============== +"unused" FileName_BTS - Name of the Full field wind file to use (.bts) +================== Parameters for Binary Bladed-style Full-Field files [used only for WindType = 4 or WindType = 7] ========= +"unused" FileNameRoot - WindType=4: Rootname of the full-field wind file to use (.wnd, .sum); WindType=7: name of the intermediate file with wind scaling values +False TowerFile - Have tower file (.twr) (flag) ignored when WindType = 7 +================== Parameters for HAWC-format binary files [Only used with WindType = 5] ===================== +"unused" FileName_u - name of the file containing the u-component fluctuating wind (.bin) +"unused" FileName_v - name of the file containing the v-component fluctuating wind (.bin) +"unused" FileName_w - name of the file containing the w-component fluctuating wind (.bin) + 64 nx - number of grids in the x direction (in the 3 files above) (-) + 32 ny - number of grids in the y direction (in the 3 files above) (-) + 32 nz - number of grids in the z direction (in the 3 files above) (-) + 16 dx - distance (in meters) between points in the x direction (m) + 3 dy - distance (in meters) between points in the y direction (m) + 3 dz - distance (in meters) between points in the z direction (m) + 90 RefHt_Hawc - reference height; the height (in meters) of the vertical center of the grid (m) + ------------- Scaling parameters for turbulence --------------------------------------------------------- + 1 ScaleMethod - Turbulence scaling method [0 = none, 1 = direct scaling, 2 = calculate scaling factor based on a desired standard deviation] + 1 SFx - Turbulence scaling factor for the x direction (-) [ScaleMethod=1] + 1 SFy - Turbulence scaling factor for the y direction (-) [ScaleMethod=1] + 1 SFz - Turbulence scaling factor for the z direction (-) [ScaleMethod=1] + 1 SigmaFx - Turbulence standard deviation to calculate scaling from in x direction (m/s) [ScaleMethod=2] + 1 SigmaFy - Turbulence standard deviation to calculate scaling from in y direction (m/s) [ScaleMethod=2] + 1 SigmaFz - Turbulence standard deviation to calculate scaling from in z direction (m/s) [ScaleMethod=2] + ------------- Mean wind profile parameters (added to HAWC-format files) --------------------------------- + 5 URef - Mean u-component wind speed at the reference height (m/s) + 2 WindProfile - Wind profile type (0=constant;1=logarithmic,2=power law) + 0 PLExp_Hawc - Power law exponent (-) (used for PL wind profile type only) + 0.03 Z0 - Surface roughness length (m) (used for LG wind profile type only) + 0 XOffset - Initial offset in +x direction (shift of wind box) +================== LIDAR Parameters =========================================================================== + 0 SensorType - Switch for lidar configuration (0 = None, 1 = Single Point Beam(s), 2 = Continuous, 3 = Pulsed) + 0 NumPulseGate - Number of lidar measurement gates (used when SensorType = 3) + 30 PulseSpacing - Distance between range gates (m) (used when SensorType = 3) + 0 NumBeam - Number of lidar measurement beams (0-5)(used when SensorType = 1) + -200 FocalDistanceX - Focal distance co-ordinates of the lidar beam in the x direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceY - Focal distance co-ordinates of the lidar beam in the y direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceZ - Focal distance co-ordinates of the lidar beam in the z direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0, 0, 0 RotorApexOffsetPos - Offset of the lidar from hub height (m) + 17 URefLid - Reference average wind speed for the lidar[m/s] + 0.25 MeasurementInterval - Time between each measurement [s] +False LidRadialVel - TRUE => return radial component, FALSE => return 'x' direction estimate + 1 ConsiderHubMotion - Flag whether to consider the hub motion's impact on Lidar measurements +====================== OUTPUT ================================================== +True SumPrint - Print summary data to .IfW.sum (flag) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/example/MHK_RM1_Floating/MHK_RM1_Floating_MoorDyn.dat b/example/MHK_RM1_Floating/MHK_RM1_Floating_MoorDyn.dat new file mode 100644 index 00000000..3e3b326e --- /dev/null +++ b/example/MHK_RM1_Floating/MHK_RM1_Floating_MoorDyn.dat @@ -0,0 +1,44 @@ +--------------------- MoorDyn Input File ------------------------------------ +Floating MHK turbine mooring input properties, based on the RM1 tidal current rotor with a quad-style floating platform +FALSE Echo - echo the input file data (flag) +----------------------- LINE TYPES Chain studless 0.018m -------------------- +Name Diam MassDen EA BA/-zeta EI Cd Ca CdAx CaAx +(-) (m) (kg/m) (N) (N-s/-) (-) (-) (-) (-) (-) +main 0.324 644.8 85.4e8 -0.8 0.8 2.4 1.0 1.15 0.5 +---------------------- POINTS ----------------------------------------------- +Node Type X Y Z M V CdA CA +(-) (-) (m) (m) (m) (kg) (m^3) (m^2) (-) +1 Fixed -152.0 -50.0 -50.0 0 0 0 0 +2 Fixed -152.0 0.0 -50.0 0 0 0 0 +3 Fixed -152.0 50.0 -50.0 0 0 0 0 +4 Fixed 152.0 -50.0 -50.0 0 0 0 0 +5 Fixed 152.0 0.0 -50.0 0 0 0 0 +6 Fixed 152.0 50.0 -50.0 0 0 0 0 +7 Vessel -34.0 0.0 -10.0 0 0 0 0 +8 Vessel -34.0 0.0 -10.0 0 0 0 0 +9 Vessel -34.0 0.0 -10.0 0 0 0 0 +10 Vessel 34.0 0.0 -10.0 0 0 0 0 +11 Vessel 34.0 0.0 -10.0 0 0 0 0 +12 Vessel 34.0 0.0 -10.0 0 0 0 0 +---------------------- LINES ------------------------------------------------ +Line LineType AttachA AttachB UnstrLen NumSegs Outputs +(-) (-) (-) (-) (m) (-) (-) +1 main 1 7 160.0 30 - +2 main 2 8 152.0 30 - +3 main 3 9 160.0 30 - +4 main 4 10 160.0 30 - +5 main 5 11 152.0 30 - +6 main 6 12 160.0 30 - +---------------------- SOLVER OPTIONS --------------------------------------- +0.5e-4 dtM - time step to use in mooring integration (s) +3.0e6 kbot - bottom stiffness (Pa/m) +3.0e5 cbot - bottom damping (Pa-s/m) +1.0 dtIC - time interval for analyzing convergence during IC gen (s) +10.0 TmaxIC - max time for ic gen (s) +4.0 CdScaleIC - factor by which to scale drag coefficients during dynamic relaxation (-) +0.1 threshIC - threshold for IC convergence (-) +0 outswitch - switch to disable MD.out file, output channels can be found in the main FAST output file +------------------------ OUTPUTS -------------------------------------------- +FairTen1 FairTen2 FairTen3 FairTen4 FairTen5 FairTen6 +AnchTen1 AnchTen2 AnchTen3 AnchTen4 AnchTen5 AnchTen6 +------------------------- need this line ------------------------------------ diff --git a/example/MHK_RM1_Floating/README.md b/example/MHK_RM1_Floating/README.md new file mode 100644 index 00000000..f5d2ea72 --- /dev/null +++ b/example/MHK_RM1_Floating/README.md @@ -0,0 +1,5 @@ +This subdirectory is a demonstration of running OpenFAST with MoorDyn-F. These files are very similar to the MHK_RM1_Floating OpenFAST regression test in https://github.com/OpenFAST/r-test/tree/main/glue-codes/openfast/MHK_RM1_Floating. A few small changes were made, limiting the simulation to run for only one second and changing the output channel list for MoorDyn. The main MoorDyn output file was also disabled, as those outputs can be found in the OpenFAST output file. The changes were made to `MHK_RM1_Floating_MoorDyn.dat` and `MHK_RM1_Floating.fst`. Becasue this example is a modification of the OpenFAST r-test repository (https://github.com/OpenFAST/r-test/tree/main), that license is also included here. + +To run, you need to locate the OpenFAST executable from the OpenFAST release files, or compile it yourself. More information on this can be found in the [OpenFAST documentation](https://openfast.readthedocs.io/en/main/). Once locating the executable and moving it to this directory, run the following command. + +`openfast MHK_RM1_Floating.fst` \ No newline at end of file diff --git a/example/MHK_RM1_Floating/SeaState.dat b/example/MHK_RM1_Floating/SeaState.dat new file mode 100644 index 00000000..b85faeea --- /dev/null +++ b/example/MHK_RM1_Floating/SeaState.dat @@ -0,0 +1,72 @@ +------- SeaState Input File ---------------------------------------------------- +Floating MHK turbine hydrodynamic support structure input properties, based on the RM1 tidal current rotor with a quad-style floating platform +False Echo - Echo the input file data (flag) +---------------------- ENVIRONMENTAL CONDITIONS -------------------------------- +"DEFAULT" WtrDens - Water density (kg/m^3) +"DEFAULT" WtrDpth - Water depth (meters) relative to MSL +"DEFAULT" MSL2SWL - Offset between still-water level and mean sea level (meters) [positive upward; unused when WaveMod = 6; must be zero if PotMod=1 or 2] +---------------------- SPATIAL DISCRETIZATION --------------------------------------------------- + 30 X_HalfWidth – Half-width of the domain in the X direction (m) [>0, NOTE: X[nX] = nX*dX, where nX = {-NX+1,-NX+2,…,NX-1} and dX = X_HalfWidth/(NX-1)] + 30 Y_HalfWidth – Half-width of the domain in the Y direction (m) [>0, NOTE: Y[nY] = nY*dY, where nY = {-NY+1,-NY+2,…,NY-1} and dY = Y_HalfWidth/(NY-1)] + 50 Z_Depth – Depth of the domain the Z direction (m) relative to SWL [0 < Z_Depth <= WtrDpth+MSL2SWL; "default": Z_Depth = WtrDpth+MSL2SWL; Z[nZ] = ( COS( nZ*dthetaZ ) – 1 )*Z_Depth, where nZ = {0,1,…NZ-1} and dthetaZ = pi/( 2*(NZ-1) )] + 11 NX – Number of nodes in half of the X-direction domain (-) [>=2] + 11 NY – Number of nodes in half of the Y-direction domain (-) [>=2] + 10 NZ – Number of nodes in the Z direction (-) [>=2] +---------------------- WAVES --------------------------------------------------- + 1 WaveMod - Incident wave kinematics model {0: none=still water, 1: regular (periodic), 1P#: regular with user-specified phase, 2: JONSWAP/Pierson-Moskowitz spectrum (irregular), 3: White noise spectrum (irregular), 4: user-defined spectrum from routine UserWaveSpctrm (irregular), 5: Externally generated wave-elevation time series, 6: Externally generated full wave-kinematics time series, 7: wave frequency components [option 6 is invalid for PotMod/=0]} (switch) + 0 WaveStMod - Model for stretching incident wave kinematics to instantaneous free surface {0: none=no stretching, 1: vertical stretching, 2: extrapolation stretching, 3: Wheeler stretching} (switch) [unused when WaveMod=0 or when PotMod/=0] + 600 WaveTMax - Analysis time for incident wave calculations (sec) [unused when WaveMod=0; determines WaveDOmega=2Pi/WaveTMax in the IFFT] + 0.1 WaveDT - Time step for incident wave calculations (sec) [unused when WaveMod=0 or 7; 0.1<=WaveDT<=1.0 recommended; determines WaveOmegaMax=Pi/WaveDT in the IFFT] + 2.0 WaveHs - Significant wave height of incident waves (meters) [used only when WaveMod=1, 2, or 3] + 6.75 WaveTp - Peak-spectral period of incident waves (sec) [used only when WaveMod=1 or 2] +"DEFAULT" WavePkShp - Peak-shape parameter of incident wave spectrum (-) or DEFAULT (string) [used only when WaveMod=2; use 1.0 for Pierson-Moskowitz] + 0.314159 WvLowCOff - Low cut-off frequency or lower frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, 6, or 7] + 1.570796 WvHiCOff - High cut-off frequency or upper frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, 6, or 7] + 0 WaveDir - Incident wave propagation heading direction (degrees) [unused when WaveMod=0, 6 or 7] + 0 WaveDirMod - Directional spreading function {0: none, 1: COS2S} (-) [only used when WaveMod=2,3, or 4] + 1 WaveDirSpread - Wave direction spreading coefficient ( > 0 ) (-) [only used when WaveMod=2,3, or 4 and WaveDirMod=1] + 1 WaveNDir - Number of wave directions (-) [only used when WaveMod=2,3, or 4 and WaveDirMod=1; odd number only] + 0 WaveDirRange - Range of wave directions (full range: WaveDir +/- 1/2*WaveDirRange) (degrees) [only used when WaveMod=2,3,or 4 and WaveDirMod=1] + 123456789 WaveSeed(1) - First random seed of incident waves [-2147483648 to 2147483647] (-) [unused when WaveMod=0, 5, or 6] +"RANLUX" WaveSeed(2) - Second random seed of incident waves [-2147483648 to 2147483647] for intrinsic pRNG, or an alternative pRNG: "RanLux" (-) [unused when WaveMod=0, 5, or 6] +FALSE WaveNDAmp - Flag for normally distributed amplitudes (flag) [only used when WaveMod=2, 3, or 4] +"" WvKinFile - Root name of externally generated wave data file(s) (quoted string) [used only when WaveMod=5, 6 or 7] +---------------------- 2ND-ORDER WAVES ----------------------------------------- [unused with WaveMod=0 or 6] +FALSE WvDiffQTF - Full difference-frequency 2nd-order wave kinematics (flag) +FALSE WvSumQTF - Full summation-frequency 2nd-order wave kinematics (flag) + 0 WvLowCOffD - Low frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method] + 1.256637 WvHiCOffD - High frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method] + 0.618319 WvLowCOffS - Low frequency cutoff used in the summation-frequencies (rad/s) [Only used with a summation-frequency method] + 3.141593 WvHiCOffS - High frequency cutoff used in the summation-frequencies (rad/s) [Only used with a summation-frequency method] +---------------------- CONSTRAINED WAVES --------------------------------------- + 0 ConstWaveMod - Constrained wave model: 0=none; 1=Constrained wave with specified crest elevation, alpha; 2=Constrained wave with guaranteed peak-to-trough crest height, HCrest (flag) + 1 CrestHmax - Crest height (2*alpha for ConstWaveMod=1 or HCrest for ConstWaveMod=2), must be larger than WaveHs (m) [unused when ConstWaveMod=0] + 60 CrestTime - Time at which the crest appears (s) [unused when ConstWaveMod=0] + 0 CrestXi - X-position of the crest (m) [unused when ConstWaveMod=0] + 0 CrestYi - Y-position of the crest (m) [unused when ConstWaveMod=0] +---------------------- CURRENT ------------------------------------------------- [unused with WaveMod=6] + 1 CurrMod - Current profile model {0: none=no current, 1: standard, 2: user-defined from routine UserCurrent} (switch) + 0 CurrSSV0 - Sub-surface current velocity at still water level (m/s) [used only when CurrMod=1] + 0 CurrSSDir - Sub-surface current heading direction (degrees) or DEFAULT (string) [used only when CurrMod=1] + 12.2 CurrNSRef - Near-surface current reference depth (meters) [used only when CurrMod=1] + 0 CurrNSV0 - Near-surface current velocity at still water level (m/s) [used only when CurrMod=1] + 0 CurrNSDir - Near-surface current heading direction (degrees) [used only when CurrMod=1] + 1.9 CurrDIV - Depth-independent current velocity (m/s) [used only when CurrMod=1] + 0 CurrDIDir - Depth-independent current heading direction (degrees) [used only when CurrMod=1] +---------------------- MacCamy-Fuchs diffraction model ------------------------- + 0 MCFD - MacCamy-Fuchs member radius (ignored if radius <= 0) [must be 0 when WaveMod 0 or 6] +---------------------- OUTPUT -------------------------------------------------- +True SeaStSum - Output a summary file [flag] + 2 OutSwtch - Output requested channels to: [1=SeaState.out, 2=GlueCode.out, 3=both files] +"E15.7e2" OutFmt - Output format for numerical results (quoted string) [not checked for validity!] +"A11" OutSFmt - Output format for header strings (quoted string) [not checked for validity!] + 1 NWaveElev - Number of points where the incident wave elevations can be computed (-) [maximum of 9 output locations] + 0 WaveElevxi - List of xi-coordinates for points where the incident wave elevations can be output (meters) [NWaveElev points, separated by commas or white space; usused if NWaveElev = 0] + 0 WaveElevyi - List of yi-coordinates for points where the incident wave elevations can be output (meters) [NWaveElev points, separated by commas or white space; usused if NWaveElev = 0] + 2 NWaveKin - Number of points where the wave kinematics can be output (-) [maximum of 9 output locations] + 14.43376, -18.4752 WaveKinxi - List of xi-coordinates for points where the wave kinematics can be output (meters) [NWaveKin points, separated by commas or white space; usused if NWaveKin = 0] + 25, -6 WaveKinyi - List of yi-coordinates for points where the wave kinematics can be output (meters) [NWaveKin points, separated by commas or white space; usused if NWaveKin = 0] + -14, -17 WaveKinzi - List of zi-coordinates for points where the wave kinematics can be output (meters) [NWaveKin points, separated by commas or white space; usused if NWaveKin = 0] +---------------------- OUTPUT CHANNELS ----------------------------------------- +"Wave1Elev" - Wave elevation at the platform reference point +END of output channels and end of file. (the word "END" must appear in the first 3 columns of this line) diff --git a/example/MoorDynF_example/PtfmMotions.dat b/example/MoorDynF_example/PtfmMotions.dat new file mode 100644 index 00000000..9ba84fd9 --- /dev/null +++ b/example/MoorDynF_example/PtfmMotions.dat @@ -0,0 +1,3 @@ +# Time Surge Sway Heave Roll Pitch Yaw +0.0 0 0 0 0 0 0 +0.5 0.25 0 0 0 0 0 \ No newline at end of file diff --git a/example/MoorDynF_example/README.md b/example/MoorDynF_example/README.md new file mode 100644 index 00000000..c31bcc50 --- /dev/null +++ b/example/MoorDynF_example/README.md @@ -0,0 +1,5 @@ +This subdirectory is a demonstration of the MoorDyn-F driver. It is a useful tool if you are looking to work with the MoorDyn-F code directly without going through OpenFAST. This driver is set up to run the body.txt file from the exmple directory (the same as used in the jupyter notebook). + +To run, you need to locate the MoorDyn driver from the OpenFAST release files, or compile it yourself. More information in this can be found in the [OpenFAST documentation](https://openfast.readthedocs.io/en/main/). Once locating the driver and moving it to this directory, run `moordyn_driver md_driver.dvr` in the terminal. + +More information on the MoorDyn-F driver can be found in the MoorDyn docs [MoorDyn-F driver section](https://moordyn.readthedocs.io/en/latest/inputs.html#moordyn-f-driver-input-file). \ No newline at end of file diff --git a/example/MoorDynF_example/md_driver.dvr b/example/MoorDynF_example/md_driver.dvr new file mode 100644 index 00000000..5020a479 --- /dev/null +++ b/example/MoorDynF_example/md_driver.dvr @@ -0,0 +1,19 @@ +MoorDyn driver input file +another comment line +---------------------- ENVIRONMENTAL CONDITIONS ------------------------------- +9.80665 Gravity - Gravity (m/s^2) +1025.0 rhoW - Water density (kg/m^3) +10.0 WtrDpth - Water depth (m) +---------------------- MOORDYN ------------------------------------------------ +"../body.txt" MDInputFile - Primary MoorDyn input file name (quoted string) +"body" OutRootName - The name which prefixes all MoorDyn generated files (quoted string) +0.5 TMax - Number of time steps in the simulations (-) +0.5 dtC - TimeInterval for the simulation (sec) +0 InputsMode - MoorDyn coupled object inputs (0: all inputs are zero for every timestep (no coupled objects), 1: time-series inputs (coupled objects)) (switch) +"PtfmMotions.dat" InputsFile - Filename for the MoorDyn inputs file for when InputsMod = 1 (quoted string) +0 NumTurbines - Number of wind turbines (-) [>=1 to use FAST.Farm mode. 0 to use OpenFAST mode.] +---------------------- Initial Positions -------------------------------------- +ref_X ref_Y surge_init sway_init heave_init roll_init pitch_init yaw_init +(m) (m) (m) (m) (m) (rad) (rad) (rad) [followed by MAX(1,NumTurbines) rows of data] +0 0 0 0 0 0 0 0 +END of driver input file \ No newline at end of file diff --git a/example/MoorDyn_standalone_demo.ipynb b/example/MoorDyn_standalone_demo.ipynb new file mode 100644 index 00000000..29e36faf --- /dev/null +++ b/example/MoorDyn_standalone_demo.ipynb @@ -0,0 +1,771 @@ +{ + "cells": [ + { + "cell_type": "markdown", + "id": "2431a7", + "metadata": { + "collapsed": false + }, + "source": [ + "# Starting Out\n", + "\n", + "Some reminder notes about MoorDyn:\n", + "- MoorDyn is a library driven by an external driver\n", + " - Common publicly available drivers are WEC-Sim and OpenFAST, there are also numerous private drivers that have been built\n", + " - You can also build your own driver, which is what we do here in this demo\n", + "- The driver can either represent a larger system, like a floating wave energy converter, or it can drive the MoorDyn code in simulating a stand-alone system\n", + "\n", + "For this demo, we will be running MoorDyn-C using the example cases from the [MoorDyn documentation](https://moordyn.readthedocs.io/en/latest/drivers.html#python) and the [MoorDyn-C test library](https://github.com/FloatingArrayDesign/MoorDyn/tree/master/tests/Mooring). We will drive these systems by moving the fairleads at a constant velocity.\n", + "\n", + "To run MoorDyn-F, you need to use the MoorDyn-F driver. While it's beyond what we will talk about today, instructions and example files can be found in the `MoorDynF_example/` directory.\n", + "\n", + "P.S. If this notebook is not running, make sure the moordyn_env python kernel is selected" + ] + }, + { + "cell_type": "code", + "execution_count": 2, + "id": "627cec", + "metadata": { + "collapsed": false + }, + "outputs": [], + "source": [ + "# start by importing necessary modules\n", + "\n", + "import moordyn\n", + "import moorpy # a nice tool for visualizing moordyn\n", + "import numpy as np" + ] + }, + { + "cell_type": "markdown", + "id": "8e9e87", + "metadata": { + "collapsed": false + }, + "source": [ + "# 3-lines Simple Example\n", + "\n", + "## Input File\n", + "\n", + "For the first example, we will be simulating three catenary chain moorings on a floating wind turbine platform with no water kinematics \\(waves and currents\\). This is the mooring system of the OC3 Hywind Spar from [Jonkman 2010](https://www.nrel.gov/docs/fy10osti/47535.pdf) shown below.\n", + "\n", + "\"OC3\n", + "\n", + "These three mooring lines are attached to the platform at 70 m below the waterline and 5.2 m from the platform center, this location is known as the fairlead (represented as a MoorDyn point object). \n", + "We will run this simulation by telling MoorDyn how each fairlead is moving, and MoorDyn will output to our driver the forces at each fairlead. MoorDyn will also\n", + "produce output files that describe how the system is performing.\n", + "\n", + "This setup looks like the following MoorDyn input file:\n", + "\n", + "```\n", + "--------------------- MoorDyn Input File ------------------------------------\n", + "MoorDyn input file of the mooring system for OC3-Hywind\n", + "----------------------- LINE TYPES ------------------------------------------\n", + "TypeName Diam Mass/m EA BA/-zeta EI Cd Ca CdAx CaAx\n", + "(name) (m) (kg/m) (N) (N-s/-) (N-m^2) (-) (-) (-) (-)\n", + "main 0.09 77.7066 384.243E6 -0.8 0 1.6 1.0 0.1 0.0\n", + "---------------------- POINT PROPERTIES --------------------------------\n", + "ID Type X Y Z Mass Volume CdA Ca\n", + "(#) (-) (m) (m) (m) (kg) (mˆ3) (m^2) (-)\n", + "1 Fixed 853.87 0 -320.0 0 0 0 0\n", + "2 Fixed -426.94 739.47 -320.0 0 0 0 0\n", + "3 Fixed -426.94 -739.47 -320.0 0 0 0 0\n", + "4 Coupled 5.2 0.0 -70.0 0 0 0 0\n", + "5 Coupled -2.6 4.5 -70.0 0 0 0 0\n", + "6 Coupled -2.6 -4.5 -70.0 0 0 0 0\n", + "---------------------- LINES ----------------------------------------\n", + "ID LineType AttachA AttachB UnstrLen NumSegs LineOutputs\n", + "(#) (name) (#) (#) (m) (-) (-)\n", + "1 main 1 4 902.2 20 p\n", + "2 main 2 5 902.2 20 p\n", + "3 main 3 6 902.2 20 p\n", + "---------------------- OPTIONS -----------------------------------------\n", + "2 writeLog Write a log file\n", + "0.002 dtM time step to use in mooring integration (s)\n", + "3.0e6 kBot bottom stiffness (Pa/m)\n", + "3.0e5 cBot bottom damping (Pa-s/m)\n", + "1025.0 WtrDnsty water density (kg/m^3)\n", + "320 WtrDpth water depth (m)\n", + "1.0 dtIC time interval for analyzing convergence during IC gen (s)\n", + "100.0 TmaxIC max time for ic gen (s)\n", + "4.0 CdScaleIC factor by which to scale drag coefficients during dynamic relaxation (-)\n", + "0.001 threshIC threshold for IC convergence (-)\n", + "1 disableOutTime\n", + "---------------------- OUTPUTS -----------------------------------------\n", + "FairTen1\n", + "FairTen2\n", + "FairTen3\n", + "------------------------- need this line -------------------------------------- \n", + "```\n", + "\n", + "More information on MoorDyn input files can be found in the [V2 input file section of the documentation](https://moordyn.readthedocs.io/en/latest/inputs.html#the-v2-input-file).\n", + "\n" + ] + }, + { + "cell_type": "markdown", + "id": "d1f3b5", + "metadata": { + "collapsed": false + }, + "source": [ + "## Initialization\n", + "First, we initialize the system:" + ] + }, + { + "cell_type": "code", + "execution_count": 3, + "id": "d42146", + "metadata": { + "collapsed": false + }, + "outputs": [ + { + "name": "stdout", + "output_type": "stream", + "text": [ + "\n", + " Running MoorDyn (v2.4.0)\n", + " MoorDyn v2 has significant ongoing input file changes from v1.\n", + " Copyright: (C) 2024 National Renewable Energy Laboratory, (C) 2014-2019 Matt Hall\n", + " This program is released under the BSD 3-Clause license.\n", + "The filename is lines.txt\n", + "MoorDyn v2 log file with output level MSG at 'lines.log'\n", + "Generated entities:\n", + "\tnLineTypes = 1\n", + "\tnRodTypes = 0\n", + "\tnPoints = 6\n", + "\tnBodies = 0\n", + "\tnRods = 0\n", + "\tnLines = 3\n", + "\tnFails = 0\n", + "\tnFreeBodies = 0\n", + "\tnFreeRods = 0\n", + "\tnFreePoints = 0\n", + "\tnCpldBodies = 0\n", + "\tnCpldRods = 0\n", + "\tnCpldPoints = 3\n", + "Time integrator = 2nd order Runge-Kutta\n", + "Water kinematics for IC gen:\n", + " No Waves or Currents, or set externally\n", + "Creating mooring system...\n", + "Initializing coupled Point 4 at 5.2, 0, -70\n", + "Initializing coupled Point 5 at -2.6, 4.5, -70\n", + "Initializing coupled Point 6 at -2.6, -4.5, -70\n", + "dtM = 0.002 s (CFL = 0.015691)\n", + "Finalizing ICs using static solve\n", + " - Line1:\n", + " ID : 1\n", + " UnstrLen: 902.2\n", + " N : 20\n", + " d : 0.09\n", + " rho : 12214.7\n", + " EAMod : 1\n", + " EA : 3.84243e+08\n", + " BA : -0.8\n", + " EI : 0\n", + " Can : 1\n", + " Cat : 0\n", + " Cdn : 1.6\n", + " Cdt : 0.1\n", + " Cl : 0\n", + " dF : 0\n", + " cF : 0\n", + " ww_l : 698.333\n", + "Line 1 damping set to 9.80212e+08 Pa-s = 6.23584e+06 Ns, based on input of -0.8\n", + "Initialized Line 1\n", + " - Line2:\n", + " ID : 2\n", + " UnstrLen: 902.2\n", + " N : 20\n", + " d : 0.09\n", + " rho : 12214.7\n", + " EAMod : 1\n", + " EA : 3.84243e+08\n", + " BA : -0.8\n", + " EI : 0\n", + " Can : 1\n", + " Cat : 0\n", + " Cdn : 1.6\n", + " Cdt : 0.1\n", + " Cl : 0\n", + " dF : 0\n", + " cF : 0\n", + " ww_l : 698.333\n", + "Line 2 damping set to 9.80212e+08 Pa-s = 6.23584e+06 Ns, based on input of -0.8\n", + "Initialized Line 2\n", + " - Line3:\n", + " ID : 3\n", + " UnstrLen: 902.2\n", + " N : 20\n", + " d : 0.09\n", + " rho : 12214.7\n", + " EAMod : 1\n", + " EA : 3.84243e+08\n", + " BA : -0.8\n", + " EI : 0\n", + " Can : 1\n", + " Cat : 0\n", + " Cdn : 1.6\n", + " Cdt : 0.1\n", + " Cl : 0\n", + " dF : 0\n", + " cF : 0\n", + " ww_l : 698.333\n", + "Line 3 damping set to 9.80212e+08 Pa-s = 6.23584e+06 Ns, based on input of -0.8\n", + "Initialized Line 3\n", + "Remaining error after 52 s = 0.0014854 m/s2\n", + "Best score at 52 s = 0.0014854 m/s2\n", + "Water kinematics for runtime:\n", + " No Waves or Currents, or set externally\n" + ] + }, + { + "data": { + "text/plain": [ + "0" + ] + }, + "execution_count": 3, + "metadata": {}, + "output_type": "execute_result" + } + ], + "source": [ + "# Create the MoorDyn system from the input file\n", + "system = moordyn.Create(\"lines.txt\")\n", + "\n", + "# Set the initial positions in this driver code to what was defined in the input file\n", + "x = np.array([ 5.2, 0.0, -70.0, -2.6, 4.5, -70.0, -2.6, -4.5, -70.0])\n", + "# Formerly:\n", + " # x = []\n", + " # x += [ 5.2, 0.0, -70.0]\n", + " # x += [-2.6, 4.5, -70.0]\n", + " # x += [-2.6, -4.5, -70.0]\n", + "\n", + "# Set the velocities to zero. 3 coupled points x 3 DoF per point = 9 DoF\n", + "xd = np.zeros(9)\n", + "# Formerly:\n", + " # xd = [0] * 9\n", + "\n", + "# Setup the initial condition\n", + "moordyn.Init(system, x, xd)" + ] + }, + { + "cell_type": "markdown", + "id": "db2aee", + "metadata": { + "collapsed": false + }, + "source": [ + "## Time Stepping\n", + "\n", + "Then we run the simulation, moving the fairleads at 0.5 m/s in the x direction:" + ] + }, + { + "cell_type": "code", + "execution_count": null, + "id": "45924a", + "metadata": { + "collapsed": false + }, + "outputs": [ + { + "name": "stdout", + "output_type": "stream", + "text": [ + "Tensions at the fairleads:\n", + "FairTen1 = 827414.2252929022\n", + "FairTen2 = 939998.8305276999\n", + "FairTen3 = 939998.8305276999\n" + ] + }, + { + "data": { + "text/plain": [ + "0" + ] + }, + "execution_count": 4, + "metadata": {}, + "output_type": "execute_result" + } + ], + "source": [ + "# Make the points move at 0.5 m/s to the positive x direction\n", + "for i in range(3):\n", + " xd[3 * i] = 0.5\n", + "t, dt = 0.0, 0.5\n", + "\n", + "# Run the simulation for five timesteps\n", + "for i in range(5):\n", + " f = moordyn.Step(system, x, xd, t, dt)\n", + " t += dt # update the time\n", + " x += xd * dt # update the position \n", + "\n", + "# Print the last output fairlead tensions on the lines (the vector sum of the forces returned by moordyn)\n", + "print(\"Tensions at the fairleads:\")\n", + "print(\"FairTen1 = \", np.linalg.norm(f[0:3]))\n", + "print(\"FairTen2 = \", np.linalg.norm(f[3:6]))\n", + "print(\"FairTen3 = \", np.linalg.norm(f[6:9]))\n", + " \n", + "# Alright, time to finish!\n", + "moordyn.Close(system)" + ] + }, + { + "cell_type": "markdown", + "id": "4acdd5", + "metadata": { + "collapsed": false + }, + "source": [ + "## Visualizing\n", + "\n", + "MoorPy, a quasi-static mooring solver, can be used to visualize the outputs of MoorDyn. The details of MoorPy are beyond the scope of this example but can be found on the [MoorPy docs page](https://moorpy.readthedocs.io/en/latest/). In order to make the MoorDyn system compatible with MoorPy visualization, we need to output the line node positions. This is why we included the **p** flag in the LineOutputs:\n", + "```\n", + "---------------------- LINES ----------------------------------------\n", + "ID LineType AttachA AttachB UnstrLen NumSegs LineOutputs\n", + "(#) (name) (#) (#) (m) (-) (-)\n", + "1 main 1 4 902.2 20 p\n", + "```\n" + ] + }, + { + "cell_type": "code", + "execution_count": 5, + "id": "14db1a", + "metadata": { + "collapsed": false + }, + "outputs": [ + { + "name": "stdout", + "output_type": "stream", + "text": [ + "attempting to read lines.txt\n", + "Mooring input file 'lines.txt' loaded successfully.\n", + "attempting to load ./lines_Line1.out\n", + "attempting to load ./lines_Line2.out\n", + "attempting to load ./lines_Line3.out\n" + ] + }, + { + "data": { + "text/plain": [ + "(
, )" + ] + }, + "execution_count": 5, + "metadata": {}, + "output_type": "execute_result" + }, + { + "data": { + "image/png": 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", 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" + ] + }, + "execution_count": 5, + "metadata": {}, + "output_type": "execute_result" + } + ], + "source": [ + "# Create a MoorPy system (this loads the moordyn outputs found in /_#.out, where is either Line or Rod and # is the corresponding number)\n", + "ms = moorpy.System(file=\"lines.txt\", dirname=\"./\", rootname=\"lines\", qs = 0, Fortran = False) # qs tells MoorPy it is loading a MoorDyn system, Fortran = False tells it to use the MoorDyn-C output format\n", + "\n", + "# Plot the results at t = 0 in red\n", + "ms.plot(color=\"red\", time = 0)" + ] + }, + { + "cell_type": "markdown", + "id": "dfe100", + "metadata": { + "collapsed": false + }, + "source": [ + "# 3-lines with Body Simple Example\n", + "\n", + "## Input File\n", + "\n", + "For the second example, we will be running a very similar setup to the previous case, but this time we will couple to a rigid body.\n", + "Similar to how the previous case is set up, we have three catenary lines. However, this time, the fairleads are attached to a rigid body,\n", + "which is then coupled to the external code. When using a rigid body, we need to be strategic about how we define positions because the body \n", + "motion controls the fairlead motion. For our setup, we define the body at `0, 0, -70`, which is the depth of the fairlead attachments in \n", + "the previous example. The fairlead locations are then defined in that body's reference frame.\n", + "\n", + "\n", + "This setup looks like the following MoorDyn input file:\n", + "\n", + "```\n", + "--------------------- MoorDyn Input File ------------------------------------\n", + "MoorDyn input file of the mooring system for OC3-Hywind\n", + "----------------------- LINE TYPES ------------------------------------------\n", + "TypeName Diam Mass/m EA BA/-zeta EI Cd Ca CdAx CaAx\n", + "(name) (m) (kg/m) (N) (N-s/-) (N-m^2) (-) (-) (-) (-)\n", + "main 0.09 77.7066 384.243E6 -0.8 0 1.6 1.0 0.1 0.0\n", + "----------------------- BODIES ------------------------------------------------------\n", + "ID Attachment X0 Y0 Z0 r0 p0 y0 Mass CG* I* Volume CdA* Ca*\n", + "(#) (-) (m) (m) (m) (deg) (deg) (deg) (kg) (m) (kg-m^2) (m^3) (m^2) (-)\n", + "1 Coupled 0 0 -70 0 0 0 0 0 0 0 0 0\n", + "---------------------- POINT PROPERTIES --------------------------------\n", + "ID Type X Y Z Mass Volume CdA Ca\n", + "(#) (-) (m) (m) (m) (kg) (mˆ3) (m^2) (-)\n", + "1 Fixed 853.87 0 -320.0 0 0 0 0\n", + "2 Fixed -426.94 739.47 -320.0 0 0 0 0\n", + "3 Fixed -426.94 -739.47 -320.0 0 0 0 0\n", + "4 Body1 5.2 0.0 0.0 0 0 0 0\n", + "5 Body1 -2.6 4.5 0.0 0 0 0 0\n", + "6 Body1 -2.6 -4.5 0.0 0 0 0 0\n", + "---------------------- LINES ----------------------------------------\n", + "ID LineType AttachA AttachB UnstrLen NumSegs LineOutputs\n", + "(#) (name) (#) (#) (m) (-) (-)\n", + "1 main 1 4 902.2 20 p\n", + "2 main 2 5 902.2 20 p\n", + "3 main 3 6 902.2 20 p\n", + "---------------------- OPTIONS -----------------------------------------\n", + "2 writeLog Write a log file\n", + "0.002 dtM time step to use in mooring integration (s)\n", + "3.0e6 kBot bottom stiffness (Pa/m)\n", + "3.0e5 cBot bottom damping (Pa-s/m)\n", + "1025.0 WtrDnsty water density (kg/m^3)\n", + "320 WtrDpth water depth (m)\n", + "1.0 dtIC time interval for analyzing convergence during IC gen (s)\n", + "100.0 TmaxIC max time for ic gen (s)\n", + "4.0 CdScaleIC factor by which to scale drag coefficients during dynamic relaxation (-)\n", + "0.001 threshIC threshold for IC convergence (-)\n", + "1 disableOutTime\n", + "---------------------- OUTPUTS -----------------------------------------\n", + "FairTen1\n", + "FairTen2\n", + "FairTen3\n", + "------------------------- need this line -------------------------------------- \n", + "```" + ] + }, + { + "cell_type": "markdown", + "id": "3503c3", + "metadata": { + "collapsed": false + }, + "source": [ + "## Initialization\n", + "\n", + "First, we initialize the system. In this case, we will lean more heavily on the MoorDyn-C API:" + ] + }, + { + "cell_type": "code", + "execution_count": 6, + "id": "e3b168", + "metadata": { + "collapsed": false + }, + "outputs": [ + { + "name": "stdout", + "output_type": "stream", + "text": [ + "\n", + " Running MoorDyn (v2.4.0)\n", + " MoorDyn v2 has significant ongoing input file changes from v1.\n", + " Copyright: (C) 2024 National Renewable Energy Laboratory, (C) 2014-2019 Matt Hall\n", + " This program is released under the BSD 3-Clause license.\n", + "The filename is body.txt\n", + "MoorDyn v2 log file with output level MSG at 'body.log'\n", + "Generated entities:\n", + "\tnLineTypes = 1\n", + "\tnRodTypes = 0\n", + "\tnPoints = 6\n", + "\tnBodies = 1\n", + "\tnRods = 0\n", + "\tnLines = 3\n", + "\tnFails = 0\n", + "\tnFreeBodies = 0\n", + "\tnFreeRods = 0\n", + "\tnFreePoints = 0\n", + "\tnCpldBodies = 1\n", + "\tnCpldRods = 0\n", + "\tnCpldPoints = 0\n", + "Time integrator = 2nd order Runge-Kutta\n", + "Water kinematics for IC gen:\n", + " No Waves or Currents, or set externally\n" + ] + }, + { + "data": { + "text/plain": [ + "0" + ] + }, + "execution_count": 6, + "metadata": {}, + "output_type": "execute_result" + }, + { + "name": "stdout", + "output_type": "stream", + "text": [ + "Creating mooring system...\n", + "Initializing coupled Body 1 at 0, 0, -70...\n", + "dtM = 0.002 s (CFL = 0.015691)\n", + "Finalizing ICs using static solve\n", + " - Line1:\n", + " ID : 1\n", + " UnstrLen: 902.2\n", + " N : 20\n", + " d : 0.09\n", + " rho : 12214.7\n", + " EAMod : 1\n", + " EA : 3.84243e+08\n", + " BA : -0.8\n", + " EI : 0\n", + " Can : 1\n", + " Cat : 0\n", + " Cdn : 1.6\n", + " Cdt : 0.1\n", + " Cl : 0\n", + " dF : 0\n", + " cF : 0\n", + " ww_l : 698.333\n", + "Line 1 damping set to 9.80212e+08 Pa-s = 6.23584e+06 Ns, based on input of -0.8\n", + "Initialized Line 1\n", + " - Line2:\n", + " ID : 2\n", + " UnstrLen: 902.2\n", + " N : 20\n", + " d : 0.09\n", + " rho : 12214.7\n", + " EAMod : 1\n", + " EA : 3.84243e+08\n", + " BA : -0.8\n", + " EI : 0\n", + " Can : 1\n", + " Cat : 0\n", + " Cdn : 1.6\n", + " Cdt : 0.1\n", + " Cl : 0\n", + " dF : 0\n", + " cF : 0\n", + " ww_l : 698.333\n", + "Line 2 damping set to 9.80212e+08 Pa-s = 6.23584e+06 Ns, based on input of -0.8\n", + "Initialized Line 2\n", + " - Line3:\n", + " ID : 3\n", + " UnstrLen: 902.2\n", + " N : 20\n", + " d : 0.09\n", + " rho : 12214.7\n", + " EAMod : 1\n", + " EA : 3.84243e+08\n", + " BA : -0.8\n", + " EI : 0\n", + " Can : 1\n", + " Cat : 0\n", + " Cdn : 1.6\n", + " Cdt : 0.1\n", + " Cl : 0\n", + " dF : 0\n", + " cF : 0\n", + " ww_l : 698.333\n", + "Line 3 damping set to 9.80212e+08 Pa-s = 6.23584e+06 Ns, based on input of -0.8\n", + "Initialized Line 3\n", + "Remaining error after 52 s = 0.00146219 m/s2\n", + "Best score at 52 s = 0.00146219 m/s2\n", + "Water kinematics for runtime:\n", + " No Waves or Currents, or set externally\n" + ] + } + ], + "source": [ + "# Create the MoorDyn system from the input file\n", + "system = moordyn.Create(\"body.txt\")\n", + "\n", + "# You can get the initial positions and velocities from the system itself using the MoorDyn-C API\n", + "body = moordyn.GetBody(system, 1)\n", + "state = moordyn.GetBodyState(body) # tuple with (x, xd)\n", + "\n", + "x = np.array(state[0]) # x, y, z, roll, pitch, yaw \n", + "xd = np.array(state[1]) # xdot, ydot, zdot, roll_dot, pitch_dot, yaw_dot \n", + "# Formerly:\n", + " # x = list(state[0]) # x, y, z, roll, pitch, yaw\n", + " # xd = list(state[1]) # xdot, ydot, zdot, roll_dot, pitch_dot, yaw_dot\n", + "\n", + "# Setup the initial condition\n", + "moordyn.Init(system, x, xd)" + ] + }, + { + "cell_type": "markdown", + "id": "fc5957", + "metadata": { + "collapsed": false + }, + "source": [ + "## Time Stepping\n", + "\n", + "Then we run the simulation, moving the fairleads by moving the body at 0.5 m/s in the x direction:" + ] + }, + { + "cell_type": "code", + "execution_count": null, + "id": "9e27d7", + "metadata": { + "collapsed": false + }, + "outputs": [ + { + "name": "stdout", + "output_type": "stream", + "text": [ + "FairTen1 = 827414.2252929765\n", + "FairTen2 = 939998.8305276999\n", + "FairTen3 = 939998.8305276999\n" + ] + }, + { + "data": { + "text/plain": [ + "0" + ] + }, + "execution_count": 7, + "metadata": {}, + "output_type": "execute_result" + } + ], + "source": [ + "# Make the body move at 0.5 m/s to the positive x direction\n", + "xd[0] = 0.5 # 0 index is the first of 6 DOF\n", + "t, dt = 0.0, 0.5\n", + "\n", + "# Run the simulation for five timesteps\n", + "for i in range(5):\n", + " f = moordyn.Step(system, x, xd, t, dt)\n", + " t += dt\n", + " x += xd * dt # update the position \n", + "\n", + "# Print the last output fairlead tensions on the lines (the vector sum of the forces returned by moordyn)\n", + "point4 = moordyn.GetPoint(system, 4)\n", + "point5 = moordyn.GetPoint(system, 5)\n", + "point6 = moordyn.GetPoint(system, 6)\n", + "print(\"FairTen1 = \", np.linalg.norm(moordyn.GetPointForce(point4)))\n", + "print(\"FairTen2 = \", np.linalg.norm(moordyn.GetPointForce(point5)))\n", + "print(\"FairTen3 = \", np.linalg.norm(moordyn.GetPointForce(point6)))\n", + "\n", + "# Alright, time to finish!\n", + "moordyn.Close(system)" + ] + }, + { + "cell_type": "markdown", + "id": "9e7f33", + "metadata": { + "collapsed": false + }, + "source": [ + "## Visualization\n", + "\n", + "Now let's visualize with MoorPy!" + ] + }, + { + "cell_type": "code", + "execution_count": null, + "id": "861467", + "metadata": { + "collapsed": false + }, + "outputs": [ + { + "name": "stdout", + "output_type": "stream", + "text": [ + "attempting to read body.txt\n", + "Mooring input file 'body.txt' loaded successfully.\n", + "attempting to load ./body_Line1.out\n", + "attempting to load ./body_Line2.out\n", + "attempting to load ./body_Line3.out\n" + ] + }, + { + "data": { + "text/plain": [ + "(
, )" + ] + }, + "execution_count": 8, + "metadata": {}, + "output_type": "execute_result" + }, + { + "data": { + "image/png": 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a2+87trG3txd//PEHtFrtgGMb3d3dWbIXTOzHBNoNW1RUhLq6OsTFxcHf39+sbQgZxrF0OzQ+TwiBm5sb1Go1dDrdiOyV+6LRaJCTkwOJRIK0tDTIZDIEBATwIR+avKusrIRYLOYTvd7e3v0S2GPBRA7jjEa1jy3vzBwdHUEIQVRUFORy+YQZ2/ivf/0LL730EhoaGhAfH48333wTaWlpNtsfE/tRhuM4dHR0ICcnB4QQzJ49G87OzmZvZ6xj9q2trcjOzoaPjw+mTJmClpYW1NTU8GZZCoWCD8EMJyRtbW3Izc2Fr68voqKi+oV8ZDIZ3NzcEBISAr1ez4/hq66u5vdHyztHsj9bMFHvGoDRidnb8oJMfwdUuCfC2MYdO3Zg48aN2LZtG9LT0/Haa69h8eLFKCkpMdu9dqQwsR8lqCVxXV0dSkpK4O/vj+joaItXPGPZ/VpdXY3i4mKT+Ly3tzeAc/HUlpYWtLS0IC8vDwaD4VzFDcfBp6ICjsuWQWx0caupqUFJSQkiIyMREhIy4P6MQz400evj48OHkGiit7CwEHq9Hp6envyqnw7mMP68toLV2Y/N9g0GAwAMuI/BxjbSxQId2yiXy3H69Gnk5+dj3rx5uPTSS212vADwz3/+E7feeituvPFGAMC2bdvwzTff4P3338cjjzxik30ysR8FaDdsdnY2mpqaMHPmTAQHB1u1TSFW9oB5sX+O43j//MHi8zKZzKR+uru7Gy0tLdB8/TUUjz2GQx9/DPfp0+Ht7Y2WlhYolUokJSUNO0KRQvdH/yuVSuHs7IyAgAAYDAaoVCq0t7dDqVSivLwcUqmUL++0pehMhOElQ23/fBX7vgw2tvHEiRN45JFH0Nraiv379yM3NxcLFy5Eamqq4P0gWq0WGRkZePTRR/nHxGIxFi5ciGPHjgm6L2OY2NsYjuOgUqmQnZ0NlUoFZ2dnq4UeEE7sR1rVo1arkZWVBUIIUlNT+62YB4IOx3Bzc4Nh0iQAwJQZM6A0GFBQUACO4+Du7o62tjaIxWK4u7ubLWp9Qz400RsaGsqv4trb23HmzBn09PRAJpNBJBLBx8cH7u7ugonQRA7j2PrOwdzSS0u3b8l3RMc2rly5EsuXL8f8+fORlpaGvLw8vPbaa/jss8+waNEiQY+3ubkZBoOhX57O398fxcXFgu7LGCb2NoJ2wzY1NSEnJwdeXl4IDQ1FWVmZINsfTcdK4/h8ZGSkSf38iNFqAQByNze0lJfD19cXkydPRnt7O1paWlBVVQWRSARvb28oFAp4e3uPqAS1L31DPv7+/vD19YVKpUJubi7c3NzQ09ODuro6cBzHN+mYa+fQl4ks9hP9zkGoi4lIJIJKpcJll12GpUuXguO488rgj4m9DaBhm4qKCpSVlSEyMhJhYWFoa2sTbAzgaJiYEUJw9uxZFBcXY9q0aQgKCrI4gSX6n9ifystDRGQkwsPD+WRacHAwn0hrbm7my1FdXV2tqrWnAkMT4kFBQZg8eTI4joPBYEB3dzfa2trGvZ0Di9kPjZB3Dl1dXXBzcwMwsrCQJSgUCkgkEjQ2Npo83tjYiICAAJvsE2BiLzi0VDA3NxednZ1IS0uDp6cnAOFCL0Jua7A7BIPBgMLCQiiVSrPq5weCEAJlTQ1cRCLEJibCd4BqA+NE2tSpU6HVatHa2oqWlhYUFBRAp9PxsXcfH58RhZEA4OzZsygtLUV0dDQm/S+URKFVGUPZOVDxp3YOQ33Gibyyn8ill0JuX6VS8WJvK2QyGZKTk3Hw4EGsXr0awLnPcPDgQWzYsMFm+2ViLyAGg4EPeTg5OfUzMRNS7IUK4wx0h2Acn09JSRmxsA6ETqdDfn4+PNraQKTSAYV+IGidPZ2KpFKp0NzcDKVSibKyMshkMn7V7+3tDalUavJ+juNQWlqKhoaGQRPAA1X5+Pr68vYVtMrn7NmzAMCXdw4UYrJ1U5UtxXI0YvYTYWVPzzNbiz0AbNy4Eddffz1SUlKQlpaG1157DSqViq/OsQVM7AWAEAK9Xs+bmIWHh2Pq1Kn9fvxCr+xtEcahFyuFQoFp06ZZFp//HzQx7eTkhBA/P8DCWmvj2mk6GKOtrQ0tLS0oLy9HXl4e3N3d4ePjA4VCAScnJ+Tn50Oj0SA9PX1EsfiR2jnU1taiuLgYzs7O/Kqf3rmxlf3YbF+oi0l3dzffIGhr/va3v0GpVOIf//gHGhoakJCQgO+//97s5kpzYGJvJbR+vqCgAE1NTUhMTOTLuvoyXsM41NO+uroaJSUlVsfnAUCpVCI/Px/BwcGYOnUqyLffgljQWTsQEonEpHxOrVajubmZT/TSJp6hXEOHYyA7B29vb3AcB51Oh7a2NrS3t/N2DmKxGEqlEo6OjhbbOQyGrUNEo5GgHY1qHGtRqVQAMCpiDwAbNmywadimL0zsrYCamNE2/zlz5gxZQUJX40KsdISsxjEYDMjPz4dSqURiYqJVXaiEEFRWVqKiogLR0dEIDAw894RWC9In1CIUjo6OCA4OhrOzM1paWhAQEAAnJyfU19fzDol01W+pqZqx+EulUjg5OcHf35/viM7Pz4dKpUJmZqbgdg62DLPQu7qJsPIeavtCiH13dzfkcvm4sN+wBUzsLYCamNXU1KCgoABBQUGYPn36sCc0PSGFEHuhwjgAUFJSAgcHB6SmpsLJycniVZ7hf/XzHR0dSElJgbu7+59PajQgNvwR0U7cvolYnU7H+6IbJ3ppvN/FxcWq2v6uri6+xX3atGkm7flC2TnYcuVNFwy2vJhMlDr+rq4ui86HiQITezOhJmbFxcWora1FTEzMn6vXYTAeFmItQoRxWlpaoFKp4OHhgYSEBH72pyX09vbydzjp6en9V0cajWBhHGOGS8RKpVLe+pYm4Kidw+nTpyGVSvlV/0CJ3qFQKpXIy8tDREQEX0rKcZxVdg4DYeswDmA7sTf2rbEVQq7sXV1dBTii8QkTezOgq7acnBzo9XrMmjULLi4uI36/kGJPwy+WQAhBVVUVSktL4enpybeLU9Hz8vIy68fT1taGnJwc+Pv7D3qHI9JqLU7QDoZOp0NeXh7UavWIErHGid6wsDA+DEenIRkneofrsK2ursbp06cxY8YMk9poa+wcvLy8BrzY2LrSB7BdctkcKwNr9mGJ02pfqNizlb0dQ8M2jY2NyM3NhUKhQExMjNmrCTp2bzRtDvpCQy3Nzc18fJ7jOD7UUVRUBK1WO+KadlrHPpSRGYBzK3sLOmIHo6enh6/0SUtLs6gBqu9QDLVaza/6z549C0IIH3tXKBS8lW5JSQl/J0ErcQbDXDsHNzc3fp/0YmPLMIitwzi23j7dh1DVOKOVnB0LmNgPA+2GPX36NCoqKhAVFTW0qA2DkJ425m6nt7cXWVlZEIlEJvF5sVjMD4Ogw5+bm5vR3NzMd5Yar/odHBzAcRyKi4vR1NQ0IiMzkYBhnNbWVuTm5mLSpEmYNm2aYCsxR0dHBAUFISgoCIQQdHZ2oqWlhU/0Ojk58S30ycnJFgnDYHYOHMdBrVbzVT7Gdg69vb3Q6XSCfMa+jFbZpa0tlIXodqYx+/MVJvZDQFe8x48fh1QqRXp6umnS0QLEYrHF4Ze+2zFH7FtaWpCdnc0nEgeLzxsPf6ahDtrJWlJSArVaDQ8PD6jVaojFYqSlpY3Mj1+tFiSMQxOxUVFRCAoKsnp7gyESifg5qJMnT0Z3dzffaAYAJ06c4GPvCoXC6kQvcC7k4+LigkmTJpnYObS1teHMmTOoq6sT3M5hojdUCbmP0WqoGiuY2A8ALY9UKpXIzs6GXq/HvHnzBCnJEro+fjiM4/ORkZEICgriw0kjQSKRwNfXF76+vgCApqYmFBQUQCKRQK1W49SpU3y4Z6gEp0ittiqMw3EcysrKUF9fb5YlshB0dXUhKysLPj4+iI6OhkgkQk9PDx/yobF3445eS86VvrX9MpkMSqUSYrEYcXFx0Gg0Fts5DMZEN0EDhE3QMrG3I6hPSkVFBUpLSxEREYHy8nLBqgkkEsmohXGM4/NJSUnw8PCw6odXX1+PoqIiTJ48GWFhYeA4rl+C08PDgxd/YwESqdXgPDws2q9xInbEdxICMVDFDQD+7odOQ6IdvRUVFf06ei2xUqa9D93d3UhLS+PzBZbaOQzGRO+eBVg1zkhhYm8ENTHLz89HW1sbUlNT4e7ujvLycsFOqNGK2Q8Wn7cEQghOnz6NmpoaxMbG8qv8vgnO3t5etLS0oLm5GRUVFfzzCoUCQT09IM7OMPcIhEjEWspgFTd9EYvFJt+DRqPhV/10Ri9dgY/ESpkOugGA1NRUk7sES+0cBjt3J7oJGiCs2A/W/X4+wMT+f1C/lezsbMjlcsyePRtyuZwPlQgRZwdGZ8LUSOPzI4Guqnt7e5GWljZkAsvJyQnBwcG8ZTH1qq+oqIB3ays6urvRWV7Or3aHOyaaiA0MDERkZOSolcQRQlBaWsqHjIaruOmLXC7HpEmTMGnSpEETvcYhH2Oh6u3tRWZmJlxdXTFz5sxBRcxcOwcPDw9+f8blhedLzF4osZ88ebIARzQ+sXuxpyZmZ8+eRWFhIcLCwkwqPGi1ynjztBmo9NLa+HxfqJGZs7Mz0tLSzGo4opYB3t7e5wzVCIFGoUC9SoXq6mp+WhQN+fSNcY9WIrYver3e5OJmbciob6JXr9f3S3jT8ItcLkdJSQkCAgIwffp0s/7dhrJz6O3tRWtrK9ra2lBZWWli53A+hHGEuntQqVSsGud8hZqYFRYW8s5zNERhjEQiEXRlb4tqHBrjbW1ttdrfBuhvZGbtqlrc0wNnPz/ExcWZDCqpqqpCfn4+3NzceOFvbGxEQ0MDEhMT+UHmo4FarUZ2djZvHWHOxW2kODg49Ctzpav+zs5OSCQS6PV6NDQ0DHgRHAl9q3xkMhlcXV0REhICvV5vYufQ3d0NsViMsrIyi+0chmI07JmFdL1kCdrzEBrnpLHROXPmDBpLFUqg6baEDuPQW3+xWIyUlBSr4/PUyGy4WLU5iFUqkP8lvwYaVNLS0oKmpiZUVlaCEAIfHx/09vZCrVZbNJ7QXPpW3Nh6NQr8Weba1taG7u5uxMTEwNHRkXfvzM/PN+notTTB3re2n/ZN6PV6FBQUQKvVQqPRWGznMBS2DuMIacegUqmsLq0ez9id2NOVQF1dHfLy8hAYGDjsj1uoChoht0XDOM3NzbxVwdSpU62Kzw9pZGYNWu25pqpBVk0ymQweHh6oqKiAl5cXwsPD+WQjNRKjq36hV57A4BU3toYQgjNnzqC6utqknJSGvowTvTk5OSCE8CEf6ttvLvS7I4Tw4p6YmMjfvVpi5zAUo+FlDwgj9qyp6jyCmpiVlpaiuroaMTEx/UbVDYSQK3shrYm1Wi0yMzMxffp0TJo0yar4/LBGZtbQ0QEAIINcPAZKxPr4+GDKlCn8eMLm5mbk5eXBYDDwQ8mtHRIOnLN7KCsrE/QuZiRwHIeioiK0trYiNTV1wJK/vonerq4utLS0oLGxESUlJSaJXnOarOh5I5VKkZKSYvI+YzsHnU6Hjo6OYe0chvuctjZBA6y3YyCEoLu7m63szwc4jkNXVxdycnKg1Woxa9asEdfUjreVvcFgwJkzZ6DT6RAfHw+FQmHVyU7FdigjM0vp7gY681swFQAZoBGKlgpOnz4dwcHB/Z7vO56QCh6tbHF2drbIq97aihtr0Ov1yM3NhVarRWpq6ojCVCKRCO7u7nB3d0dERMSAiV7jjt7BDL1oyM/NzQ0zZ87s92892KjGoewcqPgPdOEdLS97Ie7GVCoVq7OfyNCwTVNTE3JycuDj44Pk5GSz6rWFTtBaI/Y9PT18/byLiwtyc3Ph7u7OT24yp5OSEIKamhqUlpYOKrbW8sXrFZj5/P2YCkAnl4K64xiL7UgTsX0Fj3rVGw8lNzYuG6ySRq/X88NGRrtJiyaBZTJZv1W1ORgnegGYdPQa9zjQPzKZDF1dXcjMzOQv6sOdJyO1c2hsbOQ9lPraOUyUOn62sp/gUBOz8vJylJeX8yZmlniYjAexHyg+r9VqedOyqqoqvsGHhjkGi7FSIzOlUmk7+wGNBkkfXIXZKAIAVOx7H7HzLhKsvHEgr3o6lLy0tBSOjo4mVg7U4oFW3JhbTmot1F/H29tb8CSws7MznJ2dERISYtLjQBO9zs7O6O3ttco8bqDafuqaSh08+9o5cBwHFxcXm9k06/V6QcS+p6cHHMed19U4IiLUuKNxBsdx6OnpQW5uLrq6upCYmAgPC9v1s7Ky+MShtZSUlMBgMGDGjBkjfg+tkCkrKxsyPm/8I29ubuYHk9BVP72112g0yM3NhcFgQEJCgm2qXdRqyNeuBQ4cQiNc4K/vgMjLAx1ff40MjQaOjo6IjY21mdjq9Xq0tbXxF0KtVgs3Nzd0d3fD29sbsbGxNu/sNIY27IWGhlo1G9cSamtrUVRUBHd3d/T29vJ5D7rqF+LOhrqBGgwGEzuH6upq6PV6iMVii+wchqO5uRlnzpxBWlqaVdtpbGzEtGnToFKpRvVObzQ571b21MSMdpG6urpi9uzZViUchQ7jaLXaEb/eYDAgLy8PbW1tw/rb9G1kooO4qX2Bg4MD3N3d0dbWBm9v7yE7NK1CrYb86qsh/vVXaL78Ah5xcagrKoLfgw/CeeVKBL33HkKWLrXp7b2DgwNv4EYI4XMDTk5OaGlpwdGjR01W/ba0YWhoaEBBQYHNQmVDQcN0cXFxfG1/d3c3mpub+UQvnaxlzXcxUMintbUVBoOB762wxM5hOISssZdKpaNS5jtWnFdiT03MTp06hebmZkydOlWQVdRYddDS+LxEIuETeeZ8FjqIm9oXlJeXo6qqCg4ODryjpzUWvQPS2wv5X/8K8bFj0OzcCe6SS0A4DnVNTch95BEs2LoVUXfeCfW334LExFi/vxFQU1ODsrIyzJw5k58YRVf9ZWVl6O3thaenJy/+Qk0rIoSguroa5eXliIuLG7Bhz1YQQlBRUYGqqiokJibyYTqRSAQ3Nze4ubnxiV5q4mb8XVDxt8RNkxCC8vJy1NbWIiUlhU96WmLnMBxs/uzIOW/EnlYL0C5SWronBGORoFUqlcjNzUVAQACmTJliVf08NTKrra1FQkICFAqFyYCS8vJyyGQyPtzT169lxKhU54T+xAlovvoK3Pz5fCK2uroaSXPmgPvhB5Dly+G4bBnU33wDMnOmRZ9pJAxWcSORSPjPCvyZ3KTfhTVzafvuu6GhAcnJyRaHEC2BTtNqbGxESkrKkHFo4zsg4Fy1TnNzs0mi1zjkM9z4P0IInwtKTU01qVsfyM7BYDCYOHj2tXMYzi6aOV6OnPNC7Oks0ezsbEilUoSHh0OlUgm2fbFYDL1eL8i2hiu9pCuy8vJyTJ8+HYGBgVbVz/e1B6Y/PmdnZ4SGhiI0NNRkpVtSUgKNRsM30gxV1WJCezvkV1wBcX4+NLt3g5s7l0/EqlQqxMTEnKu4kcuh/uYbOK5YAcelS6HeuxckMdGizzYUNPw1koqbvslNutI1tm2m4j+Sla6xPXFqauqoxoA5jkN+fj66urqQlpZmdh+Ck5MTQkJC+O+io6ODH9NYUFAANzc3Xvj7NrhxHIeCggJ0dnbyTqsDMdCoRjc3twHtHGhTHY33992n0F72bGU/TqEmZjU1NSgoKEBISAgiIyNRU1ODzs5OwfYjkUjMirMPxVAre1oS2NbWxieUrYlHdnd3Izs7Gy4uLkPaAxuvdI3HEtKqFicnJ/75AeOrSiUcL70UoupqaPbvB5eaylssOzo6Ijk5GR0dHX/+kHx8oP72W8gvuwyOy5aduwuYPdviz9kXaypujO2KIyMjedvmlpYWVFZWDljSaIxWq+W7XfvaE9savV6PnJwc6PV6QfZNk6peXl4mthYtLS18gxsVYS8vL5SVlUGj0SAlJcWsAeCD2TlwHAetVsuv+geycxCqGqe7u/u87p4FJrDY027YoqIi1NXVIS4uDv7+/gDAm0kJxWiEcXp6epCZmcmbcJkbn+8LNTILCQnBlClTRrytvmMJafNOc3OzSS07v+pvb4d8xQqIWlqg/u47kNhYtLW1IScnBwEBAYiMjBz44ublBc2+fZD/9a+QX3opNDt2gLvkEos/L6WrqwvZ2dnw8vLCjBkzrE7e9bVt7ujoMDFwo6t+KvxZWVnD2hPbAtoVK5PJzO4jGSkymQyBgYEIDAzkE73U06ikpAQikQiBgYHo6OgQNNHr7OzM51r62jmIRCLI5XI0NTVZZOdAOd9N0IAJKvb0R5eTkwOO4zB79myTW2UhxRmwfZ29UqlETk4OAgMDBYnPV1RUoLKyEjExMfwF0FL6ujTSWvbGxkac/eUXzH7ySegJQeuXX8I1Jgb1/6u2iIyM5AezD/rdublBs2sX5NdcA/kVV0D78ccwLF9u8bFSS4WwsDBEREQIfktuvNI19q6h4m8wGODs7AyFQiHYinMk9Pb2IiMjAx4eHoiJiRk1Ezc3NzfI5XI0NjbCy8sLISEhaGtr4xO9xhfCkcwvGIiBQj7UzkGj0fAWH8Z2DnTVb86EMBazH2fQOt76+nrk5eXB398f0dHR/X5UQou9kHYJxhcOaoR15swZQeLzxkZmqampgq9URCIRXF1d4erqioiuLsj/8Q8Y5HIUvvEG6lQq6A4dAgCEhoaaVJ7QVo4BP5eTEzQ7dkB2442QrVkD7TvvwLB2rdnHRj1uoqOjERgYaNkHNBPqXSOVSqFUKhESEgIHBwfU1NSgsLDQxLbZ2pDcYJjbFSskarUamZmZcHFxQWxsLMRiMb+4MA5/VVVV8X5HI030DgYN+RgMBpSUlEAqlfI9E8Z2DrW1tSOyc6DYSuxXrVqF7Oxs/s5j4cKFeOGFF3hPrsOHD+PVV1/FiRMn0NnZiWnTpuGhhx7C2j6/gZ07d+KJJ55AZWUlpk2bhhdeeAHLli0z61gmjNjTbtjS0lJUVVUhOjp60JplBwcHwcVe6JU9TV52dHQIEp/v7e3lE9SCG5n1Qfzbb5D/9a8gYWHQ7d6NCIUCXbm5UKlU8PX1RXt7O6qrq3m3Sg8Pj6E7KGUyaLdvh+yeeyC/7TZolUro77tvRMcylh43wJ9DVmJiYngjtb7xbRrDNzZwE6Keu7W1FTk5OQgPDx9Vt07gz7Cjl5fXgN3AfcNfdH4BTfS6urqamLiZc+7r9XreMsQ4ZGWJnQOlq6vLJmGciy++GI899hgCAwNRW1uLBx98EFdeeSWOHj0KADh69Cji4uKwadMm+Pv7Y//+/Vi3bh08PDywYsUK/jVr1qzBli1bsGLFCnz66adYvXo1MjMzMdOMarYJ0UHLcRw/NUmtViMxMXHIf5jOzk6cPHkSCxYsEGT/jY2NKC8vx2wBkohtbW3IysqCTCaDVCrlPcyt+aFSIzMaI7flbbxk717IbrgB3AUXQPP55+iVSnmvl7i4OD5maix2jY2N6O3tRXBwMPz8/KBQKAa+GBEC6TPPQPrii9Ddey90zz0HDPFZjCtuEhMTR7XqxdieOCEhYUi7CePRhM3Nzejs7ISLi4uJgZu5/2aNjY18o9ZoTvICzq2CMzIy+PPN3HOXOpnS88PY04h29A62TZ1Oh6ysLDg4OCA+Pn7IUBnHcTAYDP3sHNrb23k7B29vb9TV1WHHjh3w8fHByy+/bNZnMZe9e/di9erV0Gg0g+YXli9fDn9/f7z//vsAgL/97W9QqVTYv38//5oLLrgACQkJ2LZt24j3Pa5X9jRsQ2Panp6eSEpKGjbxY4swjlDb6+jogFarRUBAACZPnmx1fJ6GL0ajO1Py/vuQ3XsvDKtXQ/uf/6Ctpwc5mZkDXmSMk3lTp05FTU0Nf7wFBQUm5m18PFckgu7JJ0H8/CB78EGIlEpo334bGOBHodFo+B/9aHvcjMSe2Ji+owl1Ol2/qhZjA7fhyiVpV+zMmTN5I7TRoqOjA1lZWQgJCbG4YbGvk6mxp1FZWRlkMplJR6/xAiIzMxNyuRxxcXHD5kT6jmqkDp7Gdg5nzpzBmjVrIBKJEBoaihkzZmDRokU2+S21trbik08+wezZs4c8Xzs6OhAdHc3//dixY9i4caPJaxYvXow9e/aYtf9xK/Y0bFNRUYGysjJERkYiLCxsRCcXjbELZb4khNjTlWB5eTmAc3aq9fX18PX1tciTnQpOc3MzkpOTbRu+IATS556DdOtW6G6/HbqXXkJdYyOKiopMErFD4erqyg9AN05s0nm0VPh9fHyA9etBFArIbr0VcqUSmo8+Aozu5ISuuDEHak+s0WhGbE/cF6lUaiJ2fe0LaKkrDTdQURusK3a0aG1tRXZ2NqZOnYrQ0FBBtmmcBwoPD+d7Pvr2OXh4eKCpqQmurq6Ii4sz+998MAfPoKAgnDx5EkuWLAEhBP/9739x22234bPPPsNVV10lyGfctGkT3nrrLfT09OCCCy4wWaH35YsvvsDJkyfx73//m3+soaGhX6GFv78/GhoazDqOcSn2dEhybm4u36BhzolN/0ENBoMgJWjW2iUYx+eTk5MhkUj4krXS0lI4OzvD19eXj28PdyLTKgRCCNLT023r56HRQHbHHXD44gton34auo0bUWbUjevj42P2Jo2HchiXM1ZUVPDljIqUFEz65BN43nILHP/yF2h27QKZNMnmFTdDQe8mpFIpUlNTBTm3BrIvoKWuRUVF0Gq1fC07bTYarivWFtBpXlFRUSMa+GMpfbube3t70djYiDNnzvBWC/n5+fzK39Jzn676lUol/va3v2HmzJn46KOP4O3tjfb29iH/bR955BG88MILQ26/qKgIUVFRAICHHnoIN998M6qqqvD0009j3bp12L9/f79z9+eff8aNN96I9957DzE2sBIZV2JPTczoCsLJyckiEzMq9nq9XpAfpDUre5VKxQtESkoKH593c3NDeHg478lOQ1WEEJNVbt/PTktOqU2uTcv7WlogX7MG4lOnoPm//4Pm0kuRl5ODnp4ek27c4RiqGqdvOSM1b2tpaUGFkxM8tm5F2tNPQ3rhhah6+20UOjhgxowZo1ZxQ7GlPbExA5W6KpVKVFZWQqvVwtHREbW1tSa2zbamvr4ehYWFmDlzptWlvJZQU1MDf39/REVF8cNrqJMnzX1YYqjW1NSEFStWIDIyEp9//jn/WxvuLvmBBx7ADTfcMORrJk+ezP8//T1HRkYiOjoaISEh+OOPPzBr1iz+NUeOHMHKlSvx6quvYt26dSbbCggIQGNjo8ljjY2NZk9WGzdiT7thq6qqUFxcjPDwcEydOtXi2lyRSCR4BY25YaGmpibk5uZi0qRJg8bn+3qyGzftFBQUmFgUd3Z2oqSkBJMnTx5xSMtSROXlkF9+OURtbdB8+y1U8fHIPnkSMpnM7Bj5kKWXfehr3tbe3o7SKVMQeuedCF27Fl1PPgnNlCl8x+NorOzHyp5YJBLB0dERra2tcHR0RFpaGt/IRKdTUVsLHx8fm3wfNCdk6V2cNfT09CAjIwMKhQJRUVEQiUT8oPopU6bwCyXjhj96FzTc99HY2IgVK1YgOjoan376qVkLSmMvIXOhEQKNRsM/dvjwYaxYsQIvvPACbrvttn7vmTVrFg4ePIj7jCrUfvrpJ5OLxUgYF2JPTcwKCwvR1NSExMRE/jbOUoQsv5RIJCCEjFjsjevno6KiEBAQMKL6eeOTeerUqfwql3YL0lW/i4uLTWd7in/9FfK1a0G8vaH++We0+fgg+/hxi6t9LM2diMVieHh4oNrVFRn//CdmvfEG4v/+d5xRKnF8/nw+kUcNy2zRNTqW9sQ0bGTcFevk5MQnGY0N3E6fPi3o90FnKFRWVo5JSSut+AkMDBx02MpAw2to4tv4++ib6G1oaMDy5csRFxeHjz/+2GbJ/ePHj+PkyZOYO3cuvLy8UF5ejieeeAJTpkzhhfrnn3/GihUrcO+99+KKK67g4/AymYyf3nbvvfdi/vz5eOWVV7B8+XJ8/vnnOHXqFN59912zjmfMSy8NBgNOnz6NyspKODo6Ij4+3uoh0sC5q2V8fLwgSSy9Xo8DBw5gwYIFw54YNIHX2dmJ2NhYs7r4BoIamfX29iI8PBxdXV1QKpXQarUmtgVCfGcA4PDf/0K6cSO42bOh+fhj1P3PkmKkidiBUKlU6O7uNjsEoNFokJ2dDbFYjISEBEhFIkgfeQTSd96B9uab0fDoo2j+352Q8SqXmrdZs8o1tieOjY0dVXti4M869pF2xRonNpubm02sioeaSTsQ1CW1rq4OSUlJo54f6OrqQkZGBoKDg82y+jCGmiPSkGBPTw/eeusthIaG4pdffkFiYqJNhR4A8vLycO+99yInJwcqlQqBgYFYsmQJHn/8cb5c9oYbbsD27dv7vXf+/Pk4fPgw//edO3fi8ccf55uqXnzxRbObqsZM7GnYpq6uDjk5OXBxccHs2bMFi4X++uuviI6OtvoOATh35/Hjjz/i4osvHrLzT6VS8aVhM2bMsLp+nhqZUa8VulLrW67W0dEBFxcXKBQK+Pr6wsPDw/z96nSQPvwwpO++C93tt0O7dStOV1WhpqYGcXFxVt3Cd3d3o6enx6wywaEqbiQffADZ/feDmzULmo8/Bnx8+FVdc3Mz2traIJfLeeE3rmgZCcb2xAkJCaNqTwz82RVraR07YGpV3Nrayic+6Up3MJEjhKCoqAgtLS1ISkoadXOwzs5OZGZm8iEzoejt7cXrr7+OXbt2oaysDC4uLli4cCFuueUWLFq0SLD9jGfGJIxDTcyKi4tRW1sLf3//fvMtrUXortfhcgA0Ph8UFISIiAir6ufp9qiTZ9/VTd9yNVq33dzcjOzsbADgV3QKhWL41UtzM+TXXQfx0aPQvPkmNOvWmQzkHu0f/HAVN4Ybb4Rm2jTI166F47x50OzcCZcZM+Di4sJbNvetaBnpXdBY2hMDwnXF9rUqpqtcWvFE+xyMfWuM7ZEtLSu1hvb2dmRlZfE5KSFpbW3Fp59+itmzZyMjIwPZ2dn44Ycf0NHRIeh+xjOjvrKnrdPUijUxMRFKpRKtra1ISkoSbD/Hjx9HSEiIYGViP/30Ey644IJ+t7R0Kk9FRYVZ8fnBsNbIjCZ5lUqlyRxaWtrZN2klysqCfO1aiFQqaD75BKrk5AE7Yq2hq6sLarV6RKEQaj8wkoobUVUV5FddBVFVFbTvvgvDpZf2e43xXVBzczPa29vh7OzMXwyNW/WN7YkTEhJG1Z4YOJc0zM/PR1RUlE27YtVqNb84aG1thUgkgre3N1QqFQghSElJGfXPTivwpk2bZnG4cDDOnj2LZcuWYd68efjPf/4zqm6k44lRW9nTbtiGhgbk5eVBoVAgJiYGEokEbW1tgloSA7axOe5ba28cn09KSrI6Pq/X602GP1gSKzVO8k6bNo2/nTeeSEWF32/fPsgfeADcjBnQfP892tzdkXPiBPz8/DB9+nRB77SGu/gRQlBWVsbHiUeSayFhYVAfOgTZHXdAfs010N1/P3RPPQUYJSb73gXp9Xo+iVdQUAC9Xg9vb294eHigpqYG7u7uo25PDPxZ9TIa4wsdHR0RFBSEoKAgfl5zUVER9Ho9DAYDsrKy+IuhRSFBM6H+QbawfqiqqsKyZctwySWX4N1337VboQdGSexpN+zp06f5FXBwcDB/EgltXAbY3jLBOD6fmpoKuVxu1Y/CVkZmxrfzNLzRUlsL8W23wfGHH9CwahW6nnsOekJwOiPDqkTsYAx382gcOhluqlQ/XF2h/egjcG+8AekTT0CckQHN9u3AIPkBBwcHkwqO7u5u1NTU8NVODg4OOHPmzIgb3KzF2GNnLKpe9Ho9ysvL4erqivj4eP5iSEOChBBe+K1xqxwMOn7TFr0TlZWVWLZsGRYtWoR33nnHroUeGCWxp0PAVSoV0tPT4e7ubvK80Ktwuk1bedo3NjYiLy9PsPj8aBmZSSQS+KlUCLnrLoiKi9Hx2mtoWbgQZ8+ehUajgZOTEzQaDdrb2wVd0Q1VemlccWPxdCWRCPp77wWXmAj5unVwnDMH2k8+AZeWNszbRNBoNKivr8e0adMQGBjIx/ppOMeWQtd3Xuto+6lTi2JaACAWiyGRSPjuZmrg1tzczE+Do37xQlwMadjKFs1aFRUVWLZsGZYuXYq33357VC01xiujIvYSiYRfOQwUA3ZwcBj3Yk+3V1ZWhsrKSkRHR8Pf39/q+Dy9fbd1nBYAJF9/Ddmdd4J4eUF96BBEMTHoyM/nhZaGfKh9rHEnr7Wx+4G+I9qVKpTHDTdvHtRHj0J27bWQL1oE3bPPQr9hAzDIv89A9sTGnjUDCR39Tqy9GHIch7y8PD4RLFTp7EihDUs+Pj6Ijo4e8LMYG7hNmTLFxMk0NzcXBoOBr+5RKBRmJXRpV64twlbl5eVYvnw5VqxYgbfeeosJ/f8YtQStVqsd9Ha+q6sLx48fx8KFCwXbX3FxMTiOw4wZMwTZ3h9//MF7c8TGxsLNzc2qk8jYyCw+Pt62t++9vZA++iik770H/erV0L71FnodHQdNxBr71SiVSvT09MDT05Mv7TS3hr29vR0cx/FNIgB4wbBJV6pWC+mTT0L6xhswLF0Kzb//DRiVjppjT/znJrV8eKO5uZkfxjGYrcVQ6PV6ZGdnw2AwIDExcdSTobS0c6iGpeEghKCrq4sv7+zo6OCndA3nUV9bW4uSkhLEx8cL3pV7+vRpLF++HKtXr8brr7/OhN6IcSH2PT09+OWXX7B48WLBfvRlZWVQq9WIjY21elvd3d04duwYHB0dkZSUZHV83tjILD4+3qYlbqLiYsjXrYPo9GnoXnwR+ptvRvv//HVGmoilK36lUmlSw+7r6zuiwRNtbW0AwIuqORU31iD+/nvIb7sNRC6H9sMPwc2ZY2JPnJiYaFHoxHgYR3NzM7q6ukxsLdzc3IYMW9Gu2OH82G0BLW8UeuCJsXWBsUc9FX+ahzG2XzC++AtBaWkpli9fjiuvvBKvvvoqE/o+jAux12q1OHToEBYuXChYy3tFRQU6OjqQkJBg1XZofN7JyQldXV3w8vLivTEsqcEeNSMzQiD5v/+D7MEHQUJDodm+HWTmTP72mZa4mftjp0leWtpJq1lohc9AcW0q9p6ennzFjVDdzcMhqq2F7KabzvUQPPooTv3lL9D8r+RXqIusRqPhhb+1tRVisZgXfuM2fXO7YoWGVr3YorzRGONh5LTc1cnJCTKZDJ2dnUhMTBRc6IuLi7FixQpcffXVePnll5nQD8Coib1OpxvUJnikHarmUF1dDaVSieTkZIveT1vGjePz1KuG/qjpbSvtWh3uBKurq0NRURHvB26zkramJsjuvhsO+/dDf8MN0L70EoiTE06fPi1IRyyF/qip8Hd2dsLV1ZUXftqs09raCo7jUFtbi+7ubiQkJIxuo5ZeD9Fzz8HxlVfQGRMD8UcfQTJtmk12RRuYqNDRPgc3NzfU19cjMDBw1GfFAuea9PLy8sbEMVSv16OoqAhNTU18fs7YwM1aa4uioiKsWLEC1157LV544QWLhT48PBxVVVX9Hr/zzjvxr3/9CxdddBGOHDli8tztt99uMi2quroa69evx88//wxXV1dcf/312LJli018m8xl7I8Af3ao6vV6wcTemgStTqdDbm4uuru7kZyczMfnnZ2dERoaitDQUL5EjVoTAxg0oclxHL+itbV7oGT/fsjuugsAoPn8cxhWroRer0d+Tg5f2iiU0Bp7sU+ePBlarZa/GFZWVoIQAnd3d3Ach+bmZri7u9s8bDUQ3Wo1shYsQMjUqYjasgWiuXOhffFFGNatGzR5aylisRje3t7w9vbm+xyqq6tx9uxZAOdEl+M4m5q39aWurg7FxcWIjY0d9clW1FCtpaUFaWlpcHV1RU9PD3+e0NmwxoZl5nwnhYWFWL58OW688UY8//zzVq3oT548aaIZ+fn5+Mtf/mIyxOTWW2/FM888w//d+O7eYDBg+fLlCAgIwNGjR1FfX49169ZBKpXi+eeft/i4hGJcrOwB4ODBg0hNTe1XlmkpDQ0NqKioMNsGlFaIODo6YsaMGSOKzxt3rdKEJg330NCFRqNBQkKC7drvOzsh27QJDv/3f9AvXw7tW28Bfn5Qq9XIzs6Gg4MD4uLibJYMpL0UWq0WGo0GOp0OXV1dvDkXIQSurq5wd3eHp6cn3N3dIZfLIZfLbWpGRe2JeduJrq4/v6cVK6B9881Ba/KFgJYXRkdHIyAgAG1tbbzQ9fb28pa8A3U3C0F1dTVOnz5tkxj5cNBGufr6eiQnJw+YH+F7P/53J0QN7UbynRQUFGD58uW49dZb8eyzzwoeurnvvvuwf/9+lJWVQSQS4aKLLkJCQgJee+21AV//3XffYcWKFairq+NLSbdt24ZNmzZBqVSOeiK+L6Mm9rQ7bzAOHz6MuLg4wU5IpVKJkpISzJ07d8TvofH54OBgREREQCKRWPTjoyuXhoYGdHR0QCKRICgoCP7+/jbpSBQfPAjZhg0QtbWdW7Fedx0gEqG9vR05OTnw9fVFVFSU4D8Gg8EAjUYDjUbD52TEYjEv4l1dXcjPz0doaCgCAgL46VzNzc2QSqVwc3ODh4cHPD094ejoCLlcDplMJthx0qHckZGR/eyJJfv2Qfa/skzta6/BsHq1IPs0hiYjB3PNNF7htrW1QSaTmcT6rcnnGI8wTEpKGnUzN0IISkpK+FDqSBc59DuhBm5SqZS/WzbOf+Tl5WHFihW444478Mwzzwj+m9JqtZg0aRI2btyIxx57DABw0UUXoaCgAIQQBAQEYOXKlXjiiSf4z/aPf/wDe/fu5f2pgHO5w8mTJyMzMxOJiYmCHqO5jIswDiB8rb05jVoDxeetqZ93dnaGo6Mjuru7ER4eDjc3NxOTMhrn9/Hxse42vrUVskcfhcPHH8Mwfz40330HEh4O4FwdM80PWJKIHQhCCHQ6HS/w9PuVyWRwcXExWaUPVHFDjcro6D2lUona2lpUVFTAzc2NX/W7urpCJpNBLpdb9P2MxJ7YsHIlelNTIbv3XsjXrj1XkvrKK4CZ038G2/9IumKNw4LGK9ySkhJoNJp+ls3m7J+6do5FsxYhBIWFhfwIRXN6CPp+J9TArby8HKdOncILL7yA+Ph47N69Gxs2bMDTTz9tk/zHnj170N7ebjKR6pprrkFYWBgmTZqE3NxcbNq0CSUlJdi1axeAwWfF0ufGmnEl9ra0NxiMweLzlkJ/6FVVVSZGZrRRx/jkzcvL48vTzB08LtmzB7L77wc0GmjefpuPP1NjtrNnzyIuLs5qi2eO43hx12g0Jqt3KvDG39dIPG6MR+/NmDGDr9dubGxETU0NnJyc4OrqCi8vL7i7u/OrfqlUOqKQGhW65OTkoVe0AQHQfv45DF99BdkDD8ApJQXaF16A4ZprLI7lW9oVK5FI+CovOpiElruWlpbyQ8gVCsWQ4/eMhXYsXDs5juP9negYTkuRSCR8LB84V0104YUXYt++fVCpVHjvvfdQXV2NO++8E2nDdEuby3//+18sXbrUxEjReIpUbGwsAgMDsWDBApSXl2PKlCmC7t8WjJrYD/cjtYVx2XBi393djczMTDg5OSElJcXq+nlqZEYtYvsamYlEIpN5qz09PVAqlfzgcRcXF5PB4wN2NdbVQfrgg3D4+mvoV66E7tVXQf63cqYeM3T/lq7o+sbegXNTgVxcXCCTyQaNPfbd/0gSwSKRCO7u7nB3d8fkyZOh0Wj4cM+ZM2dACIGbmxs8PT3h4eEBZ2dnPkzU96JskT2xSATDlVei96KLIHvoIchvuw2GL7+E9vXXQUJDh3//APtXqVRWdcWKRCK4uLjAxcUFYWFhJkPI6fi9gSybaVeuSqWyWmgtoe/+hbaXqKqqwvbt2/HAAw/gwQcfxLFjx/D999+jq6tL8P0cOHCAX7EPRnp6OoBzjVxTpkxBQEAATpw4YfIaOjvW3HmxtmBcreyFFHsHB4ch58ZS982QkBCr4vOUnp4e5OTk8DNaR5KMcXZ2RlhYGMLCwnhPeqVSiaysLL5W29fX91yFAiFwePttSJ9/HnByguajj2C47DJ+BWqciB3p/ikcx/HirtFowHEcRCIR5HI5nJ2dIZPJho0fG3vcmLt/Y+RyOe/NQssYlUolGhsbUVlZCRcXFz7c4+bmxgs/IYRvVLPIY0ehgPaDD2C46ipI770XjklJ0D3yCPT33AOMYFs6nQ45OTngOE5wi+C+Q8i7u7v5nFBJSQlv2dze3j5mFsUGgwG5ubnQaDQ22X9GRgZWrVqFTZs2YdOmTXzC9KKLLhJ0PwDwwQcfwM/PD8uXLx/ydTQsS8OUs2bNwubNm9HU1MRXPf30009wd3cXrJPfGkYtQWswGIYU89zcXDg7O2Pq1KmC7E+n0+HgwYP9GrVomKGqqgozZsyAn5+fVfF54NztZV5eHt9+brXHi9GwCaVSCZdTpxD/3ntwrqqC5uabwT31FGAUB+7o6EB2drZZiVgae9dqtdDpdLzjo3GFzEi/E1rB5OnpadNmIepL39TUhJaWFkilUri7u8PJyQm1tbXw8PBAbGys1XXb6OqCdPNmOLz9NsjUqdC++iq4+fMHfflYdsXqdDo0NTWhrKwMer0eYrHYxMZhNFb3BoPBZD6F0NVVJ0+exOrVq/HYY4/hwQcftGmPAsdxiIiIwJo1a7B161b+8fLycnz66adYtmwZfHx8kJubi/vvvx/BwcF87b3BYEBCQgImTZqEF198EQ0NDbjuuutwyy232FfpJfWVGYzCwkKIxWJERUUJtr++jVp09dXT04OZM2cKEp+nFRfR0dGCDUrhaWiA7O9/h8Pnn6MnLg5Fd9+NWj8/Ptzj6+sLlUo1okYtOh2MruANBgNEIhGfCJXL5RaJlE09boaA9jnU1dWhsbERHMfBw8MD7u7u8PLy4kNOliZ5AUCUlwfZffdB8scf0F99NbSbN/dL4NKuWE9PT0HM3MyFXmjkcjliY2NNKnw6OjpMzNusnbcwENTnhxCCxMREwfsGjh8/jssuuwxPPPEENm7caPPz68cff8TixYtRUlKCyMhI/vGzZ8/i2muv5cN0ISEhuOyyy/D444+blItXVVVh/fr1OHz4MFxcXHD99ddj69at46KpatyIfWlpKbRaLWbOnCnYPn/44QdceOGFcHZ2RldXF7KysuDk5DTi+vmhMBgMKC4uto2RWW8vHN58E9JXXgHkcmifeeZcAlYshk6n41f8SqUSHMfBx8cHwcHB8PHxMRFsvV7PCzwtjZRIJLy4y2Qyq74DWnFjkwvdCGhubkZubi4iIiLg7e3Nr/ppez6N9Zub5DWB4yD56CPInngC0Gige+ihc06ajo7o7OxEVlaWVYZi1tDb24vMzEy4u7sPeEdl7FLZ3NxsYtmsUCisDrXodDpkZWVBIpEgISFB8DuaY8eO4fLLL8fTTz+Ne++9d9S/3/ONURN72nQzGOXl5eju7kZ8fLxg+zxw4ADS09OhUqmQl5eH0NBQhIeHWx2fV6vVyM3NBQDExcUJd6vMcZB88QWkTz4JUUMD9LffDt0jjwB9eg9oIrCzsxOTJ0/mLQvUajW/unV1deU/J02qWrPKNYaWqtbW1graG2EO1DlxxowZ/ZJf1KuGJr9ppy+t6Xdycho0yTsora2QbtkCh3ffBQkKQtsjj+CP4GBETJ6M8P+Vu44mdHiOQqFAVFTUiKqUjM3bOjs7+Tm0xtYWI0Wn0yEzM5N3TRVa6H///XdceeWVePbZZ3H33XczoReAcSP2VVVVaG5uttjLZiAOHToEhUKBxsZGweLztFGJ+oALdZKLjx6F9NFHITl1CvpVq6B79lmQAfIXfTtiJRIJNBoN1Go1Ojo60N7ejvb2dvT29sLd3R0BAQHw8/Mb0onRHIwrbhITE0d9GLm59sQcx/Fdqw0NDejt7YWLiwvc3Nzg5eUFV1dXszp5RaWlIA88AOdDh9CbkgLRq6+CE3B28kjo7OxEZmYmgoKCMHXqVIv+XWnVE21gMmd+gVarRUZGBpycnBAXFyd4aOjXX3/FVVddheeffx533XUXE3qBGDdiX1tbi9raWsHqZXU6HX7++WdIpVIkJCTA1dXV6pOSGplZ6hg5EKLsbMieeQaSH34Al5AA7dat4C68cMDXdnR0ICsrC97e3nwFj16vh0gkglQq5VfvUqnUxKemubkZDg4OJtU9llykjCtu4uPjR73iw1p7YuP69cbGRr5Dkwq/cbhnsDAfzdGktrfDd8sWiAsLob/sMuieeAJk+nShPuqgGFsUR0RECLJN4/kFxuZtVPxdXV3572Kg6VZC8ssvv+Cvf/0rtm7divXr1zOhF5BRE3vgnFgMRkNDA86cOYPZs2dbvR86nEGn08HJyQmBgYHw8/OzuO6ZGpnV19cjNjZWECMzUXExpM89B4fdu8FNnQrd44/DcMUVwAA/HoPBgJqaGhQWFiIwMBD+/v79Yu9D/ejo6pa6U2o0Gt6W2NfXd0T10KNVcTMYdLi7RqMRzJ6YerA3NTWhqakJer0erq6ufLjHOMkrkUj4O4rExMRzORq9HpJPP4X0+echqq2F4dproXv0UbPr80cKzVEMZP8gJNTdlcb7JRIJH+qprKyEl5cXYmJiBBfiI0eO4K9//SteeeUV3HrrrUzoBWbciH1zczMKCwsxb948q/ZRX1/P+7EEBgaaeI8YV7GMNEap1WqRl5cHrVaL+Ph4qzsSReXlkL7wAiSffQYSFATdo4/CsHYt0Kc8VKfTQavVQq1Wo6KiAo2NjZg+fToCAwOtMg8jhEClUvEJ3s7OTr5iw9fXd8Bwz1hV3FBoxYlUKkV8fLxNKhtoTJvG+Ts6OuDk5AR3d3d4eHhAqVSiq6sLKSkp8PT0NP0ONBo4/Pe/kL7wAtDZCf3NN0P3wAOAgFbC1FDNeITiaEDLgOvr61FfXw9CiImNg1DmbYcOHcKaNWvw6quv4uabb7Z4m0899RSefvppk8emT5+O4uJiAOcuZA888AA+//xzaDQaLF68GG+//baJzcF4tim2hlEV+6EGmNDb04svvtiibdM2+erqasTExMDX19ckPm9cxUJXK1T4vb29B1ypdnV1IScnB25uboiJibHqH1uUnw/pyy9D8tVXgEIB3cMPQ3/TTcD/VtXGtgRarZZvCKusrIRarUZycrJgjqDG0HAP/V4cHBz478XLywv19fVjWnEj9JzakUJXt3TVbzAY+O7nQZO83d3nGt9eew1Qq6G/4Qbo778fxMpBITQZPZjPj61RqVTIyMiAv78/QkJC+Fh/a2urIOZtBw4cwDXXXIM33ngDN954o1UXj6eeegpffvklDhw4wD9GQ5gAsH79enzzzTf48MMP4eHhgQ0bNkAsFuP3338H8GetfEBAAF566SXepvjWW28dF7Xy1jBuxL6rqwt//PEH/vKXv1i03ZycHPT29iI2NnbY+DwNazQ1NUGpVEKv1/MrW4VCAalUyjsmhoWFWbWaFZ88CYeXXoLDN9+ACwmB/v77oV+3DnByMmlsovkMGnsnhKCgoAAODg6jFh83DvcolUr+Tiw0NBRhYWGCt78PRz974lG+o6B9GQaDAWFhYWhvb0djYyN6enp4H3/ayWucL0F7OxzefRfSt94COjpguOYa6B54YMCE+3BUVVXhzJkziI+PH5Oqp+7ubmRkZGDSpEn9ksEGg8HEspnaExubtw33b/bDDz/guuuuw7/+9S+sW7fO6n/jp556Cnv27DFxnqR0dHTA19cXn376Ka688koA5yZcRUdH49ixY7jgggvGvU2xNYyb+xJqhDaYvcFg0Pi8i4sL36Y93Ptpl6GPjw+ioqLQ1dUFpVKJqqoqFBQUQC6XQ6PRYPr06ZaNb+M4SL7/Hg5vvQXJkSPgIiOh2bYNur/+Fdr/NTdpurp4WwKZTMb7u0skEr4jVqFQIDo6etRWs/R78fT0hFqtBiEE/v7+aG9vR3V1NV+q5+vra5K0swVD2ROPBhqNBpmZmZDL5UhMTIREIkFAQACmT59u0slbVFQEmUxmUtPv5OQE+b33QrZ+PaTvvw/p669D8vHHMFx+OfR33w0uJWXY/VNDu5qaGpvd1Q0HrfoJCQkZcMFDY/l01axSqfhVf1lZGRwdHfnnvby8+q36v/vuO1x//fV45513cO211wo6f3rSpElwdHTErFmzsGXLFoSGhiIjIwM6nQ4LFy7kXxsVFYXQ0FBe7I8dO4bY2FiTsM7ixYuxfv16FBQUjLlNsTWMqtiL/ufKOBD0RDAYDCMOl9D4PPWXsaR+3tiIKywsDDk5Oejq6oK7uztKSkpQU1Mz8jh/VxccPv4YDu+8A3F5OQwpKej58EOoFi+GRq+H7n/eJQ4ODnwYoG+TT0NDAwoLCzFlyhTbji4cBDoMXSQS4YILLuBXMsa16xUVFZDJZPyd0GBhMEupqqoa0p7Y1gzVFSsSieDq6gpXV1eEh4ebeBpVV1dDr9fzds1eXl5wXrcO8uuug+sXX0D2r3/Bcf58GC64APq77oJh1SqTXA2FesE3NTUhJSVl1C2KgXOr4MzMTERERIy4j4CatxlbNjc3N6OoqAharRbe3t6oq6vDlClTUF5ejhtuuAHvvfce1qxZI9h5np6ejg8//BDTp09HfX09nn76aVx44YXIz89HQ0MDZDJZvwZIf39/3oJ4vNsUW8O4WtkD56ouhhP74eLzltDT04Ps7GzI5XLMmTMHUqnUJM6fmZk5aJxfVF4Oh3ffhcP//R+gUkG3ahW6Xn8d3TNnnrMl6O2FTCbja7oH+nzG9eNjJXLGFTczZswwWYnJ5XIEBQUhKCiIv31XKpUoLCyEXq+Hj48PL/6W3uqaZU9sI+hqdtKkSSPqipVKpQgICOAtrGkJY2NjI86ePQtnZ+dzpZ2LF8N19Wp4/PorXN97D/LrrgMXGgr9HXdAf911fOMcx3EoLCxEe3u7Vc6Z1kDDZ3TBYQl9LZvp3dBLL72E/fv3Qy6X46KLLoKfnx90Op1g4ZGlS5fy/x8XF4f09HSEhYXhiy++GJPvcjwxbsReLBZDLBYP63xJ4/NqtZpf9Vi7qqTVJvQHTrcnlUoRGBiIwMBAk3h2UVERDCoVpublIeT77+H0xx/gvLzQfd11aFuzBvrAQLNsCQwGAwoKCtDR0TEmwyaAP7+DkcTHjW/fo6Ki+A7es2fPorCwEO7u7vwPfaTVGhbZEwtMS0sLcnJyMNnCrliRSARPT094enpi6tSpJkne0tJSiMViuIeGwuONN+B79ix8PvoITk8+Cekzz8Bw2WXQ3nADcl1c0KtWIzU1ddRzJMCf34GQ4TPju6Grr74av/zyC2688UZ0dnbi+uuv543FbIGnpyciIyNx+vRp/OUvf4FWq0V7e7vJ6r6xsZGvcBrvNsXWMOphnKEYzoOexuddXV2RnJxstbcLnWh0+vTpYatNeDfBxkbM3LcPkk8+gaS9HS0xMci+8060L1gAn+BgBAYGQuHhMeJQFO2IlUgkSE9PH5MEUG1tLZ+oMrfipu/QcY1Gw9fznzlzBnK5nI/ze3l5DXhhphdwi+2JBaChoQEFBQWCVh05OjoiODgYwcHBJndDDQ0NqNDr4XbbbfC56SaEHDwIr6++gvNnnyE+NBTiO+4AiYzkK7VGC1rHHxUVZZPKq927d+O2227D9u3b+QQpIcSm4ZHu7m6Ul5fjuuuuQ3JyMqRSKQ4ePIgrrrgCAFBSUoLq6mp+VvV4tym2hlGtxhluDu2RI0cwc+bMAZuW6urq+OoYS+PzxhgMBr4bMz4+fsiQgai2FqIvvoDDjh1wyMuDwccHXZdfju6rr4YkOpqfQNXS0mJWPf9YJWIp1OOmpqbGJtUeNG5LxX+gcA8186IdmaNpD0wZblas0Bj3OjQ1NaG1tRXEYIB/YSFmHj0Kz59/BkQi6BYtAnf11eCWLQNsbFXc1NSEvLw8m9TxE0Kwa9cu3HHHHfj4449x2WWXCbp9Yx588EGsXLkSYWFhqKurw5NPPons7GwUFhbC19cX69evx7fffosPP/wQ7u7uuPvuuwEAR48eBTD+bYqtYVTFfjhP+99//x3Tpk3jr6jAuRhmaWkpampqEBMTA4VCYXV8Xq1W80nI+Pj4AW+XSUsLRF99BYedOyE9dgxEJkPPJZdAfdll4JYuhdzNbcDGppHW89NE7OTJkxEWFjbqiVgaOurs7BwVjxtCCF/1pFQq0d3dDVdXV/T09MDX13dMunKNK14SEhKEdS4dIRqNBhkZGRCLxXBycoJSqYRDSwumnjyJoMOH4VJUBM7NDdqVK8GtWQPMnw8IfEGkdzWxsbEmvz0hIIRg586duOuuu/Dpp5/i0ksvFXT7faFhopaWFvj6+mLu3LnYvHkzPzaQNlV99tlnJk1Vxhe48WxTbA3jSuz/+OMPhIaG8reQxvH52NhYuLi4WC0I1MhsoNU0qagAvv4aDt98A9nx4wAhUM+ZA/Xll4OsXg2ZQmHW/vvWret0Ovj4+IAQgpaWFsTFxY1JIlar1fJ1yAkJCWMSNqmrq0NhYSGcnJygVqshl8v5i6Knp6fNhZ/jON6iOikpaUzyJL29vcjIyDCp+jH2qWlqagJXVIQpf/yBoCNH4FRXB4NCAc3ixeBWroRo4UKIrEw61tXVobi4WJB5xX0hhGDHjh2455578Nlnn2HlypWCbp9hHuNK7E+dOgU/Pz+EhobyXuGurq6Ijo62Oj4P/Bmb5o3MCIEhIwPi/fsh/fZbyAoLQWQyqGfPhm75cpBVq+AQFCTIqptWahQWFqKnpwfAueSRr6+vVb495kIrbjw8PBATEzMmYZO+9sQGg4Gvzzb26DduchMSg8GAvLw89PT0ICkpadRntQJ/zj/28/PD9OnTBz3Hent7z30vTU3Q//47gk6eRNCJE3CuqQHn4gLNxRdDv2IFREuXQmymWNfU1KC0tBQJCQmCh/AIIfjss89w3333YceOHcOO+GPYnlEV++EGmGRnZ8PDwwNyuRwFBQUIDw9HaGio1fF5GgpqaGhAbGgoPE+dguT77yE7dAgOSiUMbm7QLFwIw/LlwJIlkAxjm2sJNHREHSMNBgO/4rfUt8dczKm4sQUjsSc29qhpbm5Gd3c3PDw8TKp7rEGn05lMVhL6QjISaHlncHCwWf8OfA6kqQmqU6eg+PVXBGdkwKO0FEQshjYlBbpFi0CWLYMkLo6fTzwQ1dXVKC8vH5FNtLkQQvDJJ59g48aN2Llzp0k5JGPsGFdin5ubC5VKBZVKJVh8XqvRoGT3bnj8/jvC8vPhmJkJkV4PbWQkdAsXgixdCtHcuRDZMJTR0dFh4oHfN0RBG3PobFVa2ujn5ydYw5I1FTdCYKk9sVqt5i+Kra2tcHJy4qt7zA330K5YR0dHmwzcGAm0hp3maizFePB4W34+nA8fxqSsLPjm5ECiVkMfFATNX/4CbulSiC+5BCKjUtaKigpUVlYiKSlJ8F4GQgg++ugjPPTQQ/jyyy+xePFiQbfPsJxxI/ZarRa///47OI5DcnKyVe34pLsb5OBBGPbtg/Snn+Dc3AzO0RHaOXOgX7wYWLoU4smTrfkoI4a2/Y80ETtYnJ+ubM1didq64mYkCGVPrNfrTap7OI7j6/2HC/fQyU6jbahmjFKpRF5eHqZPn46goCBBt01HECrPngU5fBj+J08iMDMTTg0N4BwdobnwQugXLcLZuDhU6vVISkoS3IKBEILt27dj06ZN2L17t4ktAWPsGVWxH2yACb2tlUql6OrqgqenJ/z8/MyKZRtKSyH69ls4/PgjZMeOQazVotvfH93z58Plyishvvhik9WNraEhi6qqKsycOdOiKge6eqOGbd3d3Xyc39fXd9jGo9GuuBkIW9kTG3erKpVKqFSqQb8bc7tibQGteJk5c2a/dnyhoUleGu5x//VXBGVlwbOwEGKOgzoqCvrFi0GWLYP4ggsgEmhU5fvvv4+///3v2LNnDy655BIBPglDSMZc7Gtra1FYWMjH52npYlNTE9ra2uDq6sonMfuu9g0//ADxd99BdvAgpGfOgEil0FxwAZqSknB6+nRMXrIEfjb+YQ2EcUdsQkIC3NzcBNkuTdbR72aoOP94qLgZTXvi3t5efsXf2toKZ2dnKBQKyOVynD59GlOmTBmTWbHAn4lQW1S8jISenh4UFBRAVVMDRUYGArOyEJCZCWlnJwze3tBcdBEMS5ZAvHo1RBYsCAgh+M9//oMnnngCe/fuxUUXXWTxsW7ZsgW7du1CcXExnJycMHv2bLzwwguYbjQF7KKLLsKRI0dM3nf77bdj27Zt/N/PV096axgzsec4DiUlJaitrR00Pm8s/M3NzXx5np+fHzw9PSFNTYW4vR2aBQvALV4M7uKLUVBVhe7ubn4U4WhjXMNvS5E1NuBqbm6GWCw2mTyVm5sLd3f3Mau4GUt7Yr1ej5aWFlRXV6O9vR0SiQR+fn4jmq8qNJWVlaioqLBJInQkEEJQVFSElpYWJCcnQy6XnztvGhqg++03eB87hqDsbLhWVqKtsBCOZrq8EkLw73//G08//TT27t2L+fPnW3W8S5YswdVXX43U1FTo9Xo89thjyM/PR2FhIX9netFFFyEyMhLPPPMM/z5nZ2c+LHU+e9Jbw6iKPQDevz07OxsajYb3nx9ODGh5Ho1li0Qi+IvF8Jk+Hd4+Pvx8VLlcjri4uDGrssjOzoa3t/eoxoWN4/yNjY3QarVwdnZGRESEVcZkljLW9sQAeBuM2NhYSKVS/rzp6emBl5cXX9ZpKw8emiupra21SXx8pMdQUFCA9vZ2pKSk9MuV0Ea35uZmtJeWotXBgZ9aRscQDvW7JITgnXfewbPPPov9+/fjwkFmJ1uDUqmEn58fjhw5wk+xu+iii5CQkIDXXnttwPecz5701jDqYt/U1ISsrCy4u7sjKirKovp5OiqNtpvToSg+Pj6IiYkZk39McxOxtqC2thZFRUX8IGpL4vzWMtb2xMN1xdKB47Tk1dnZmf9uPDw8BOupMG7YGotcCcdxvLEcXdEPh/GQ+paWFojFYl74fXx8TEIghBC89dZb2LJlC/bv34+5c+fa5HOcPn0a06ZNQ15eHmbOnAngnNgXFBSAEIKAgACsXLkSTzzxBH9u/+Mf/8DevXtNBphUVFRg8uTJyMzMnNCe9NYw6jNoDx06hNDQUISEhFhdP0/H9p05cwY+Pj7o7e2FSqUyGaZt64YZQghfymZpIlaIYxis4qZv6aKzszP8/PwEr+c3tidOSEgYE3ti2hXb0tIyovJOOnCchsIA8GWdfcXNnGOgSfGkpKQxsdXlOA65ubno7e3lDQMt2UZ7ezt/Yezt7YWXlxfy8/ORlJSEQ4cO4cUXX8Q333yD2bNn2+BTnDuGVatWob29Hb/99hv/+LvvvouwsDBMmjQJubm52LRpE9LS0rBr1y4AwG233Yaqqir88MMP/Ht6enrg4uKCb7/91m7r/kc1W/HVV1/hpZdewiWXXIKVK1ciJSXFYrExNjJLSUnhxaWnp4d3FiwpKeHtdv38/ARfYfW1JhYqEWvJMXR2diItLa3fZ3R0dERISAhCQkJM4vyZmZkmcX5L54fSYxhre2LjrtjU1NQRXeSlUin8/f3h7+//ZwWLUony8nLk5eXB29ubF/+RiLbBYEBubi5vvz0WFsUGgwE5OTnQ6XRISUmxOJwpFovh7e0Nb29vREZG8ndE1P5AIpHg8ssvh0ajgU6ns0nY9K677kJ+fr6J0APnxJwSGxuLwMBALFiwAOXl5bwHDqM/oyr2K1euhEQiwe7du3HppZfCzc0Ny5cvx6pVqzB37twRnzDGSdD09HSTH5WzszPvjKnVavmyxfLyckFXtTRHIBKJkJaWNiY/bOOKm7S0tGFXcMaDNozj/MXFxSb1/ObE+ceDPbFxV2xqaqpFwiMWi/mB4lTcaJiwtLSUr3xSKBQDhnv0ej2ys7PBcZxVImsNBoMB2dnZMBgMSEpKEvQYnJ2dERISgksuuQTFxcW4//77UVZWhmuuuQZxcXEmq2gh2LBhA/bv349ffvll2LxPeno6APBVV+ezJ701jHrMnqJWq3Hw4EHs2bMHe/fuhV6vx9KlS7Fy5UosWLBg0NXhUEZmQ0ErNGhlD63QGMpnfTCME7HR0dFjUu3S3d2N7OxsQSpuLK3nHw/2xGq1GllZWTbtih2o8omu+L29vcFxnEkvwVh8D3q9HllZWXwVmNAlhoQQvPjii3jrrbfwww8/IOV/c3Q5juMdJoXaz913343du3fj8OHDmDZt2rDv+f333zF37lzk5OQgLi6OT9DW19fzYdV3330XDz30EJqamsZkYTYeGDOxN0av1+P333/H7t27sXfvXjQ1NWHBggVYtWoVli5dyq+kvvzyS37yTEhIiMUrc47j+FhtU1MTOI7jhU2hUAz5Y6WJWDqbcywSsa2trcjJybFZWeNI4vzUqM7f339IIy9bQrti6UV3NKqfBoplU3vi+Pj4MQlh6XQ6vinRFhcbQgi2bNmCbdu24ccff0RSUpKg2zfmzjvvxKeffoqvv/7apLbew8MDTk5OKC8vx6effoply5bxE67uv/9+BAcH87X357MnvTWMC7E3huM4ZGdnY/fu3dizZw9KSkowd+5ciMVinDhxAj/++CPi4uIE2x/txKTCr1ar4ePjw9dl07DEeEjEAn963ERFRQnecj8QA61q3dzc0NbWhoiICERERIyJ0Hd0dCArKwtBQUGYOnXqmBxDT08PTp06BblcDrFYjI6OjlExtDNGq9UiMzMTcrkc8fHxgl/wCCHYvHkz3nvvPfz0009ISEgQdPt9Gez7+uCDD3DDDTfg7NmzuPbaa5Gfnw+VSoWQkBBcdtllePzxx03KW89XT3prGHdibwwhBCdOnMA111yDlpYWSKVSTJkyBatWrcLKlSsxefJkQX9MfScIUesGhUKB9vZ2dHV1CdoRa+6xlZeX4+zZs2PmccNxHMrKylBdXQ2pVNrPini04vV0TuqUKVOsMhOzhu7ubmRkZCAgIACRkZEQiUT9BtcYh3t8fHwEX3HTwScuLi6IjY0VXOg5jsOzzz6LDz74AAcOHBB0kcUYfca12BcWFmLZsmVITU3FBx98gI6ODuzZswd79uzBkSNHMH36dKxYsQKrVq2yycmuVqtRV1eHyspKGAwGuLq6wt/fH76+vlYZtZmLccXNWHUGG9sTx8fHw8vLq1+c38PDgw/32CqcUV9fj8LCQsyYMQOBgYE22cdw0LuK0NDQQe9sjHtBlEolNBoNXxKsUCisLglWq9XIyMiAh4eHTRr4OI7DU089hY8++ggHDhxAbGysoNtnjD7jWuzr6+vx2Wef4f777zf5QdGZr/v27cOePXvw448/wtfXlxf+Cy64QJBVFE3Eenl5Ydq0aSY12XK5nBc2T09Pmwn/ePC4GYk98UBxflryKlQ4g3bFjpXHDHAuX5KdnY2pU6ciNDR0RO+hd4x01d/R0cF7Pvn6+sLNzc2s74dOuKK5CqHPPY7j8I9//AOfffYZDhw4gJiYGEG3zxgbxrXYjxSVSoUffvgBe/bswf79+yGVSrFs2TKsWrUKF110kUXZ96ESsQNZN9Afro+Pj2CrLJVKxXcbj5XHjSX2xHq9nhe2vr49ltTzG3fFJiYmjknDFnCu+zs/Px9RUVFWzQQw7lRtbm6Gg4ODSXXPUN8PTUr7+vraJDHOcRz+/ve/Y+fOnTh48CCio6MF3T5j7DgvxN4YnU6HI0eOYNeuXdi7dy+6u7uxaNEirFy5EosWLRo23m5uIravdYNOp+MHj1hjumXripuRIIQ9Mf1+aLjH3Hp+47uKsbIeAM7dZRYVFQmenDfud2hubjYJ91BTOwrNEwQGBtrEqpnjODz66KPYtWsXDh48iKioKEG3zxhbzjuxN4bjOBw/fhy7d+/G119/jerqalx88cVYtWoVX7rVd8VeWFiItrY2JCQkmG1eRY2lqLBR6wYa7hnpHUZdXR2KiopGreJmIGxhT0zr+emF0XjkoJ+fX784/3iYFQsAZ8+eRVlZGeLj4+Hj42Oz/RgXCCiVSnR2dvLGZC4uLigqKrLZxZ/jODz88MPYu3cvDh48aFL2yDg/OK/F3hjqAEhLOnNzczFr1iysXLmSn3p/55134p577sH8+fMFabzo6enhhb+jowPu7u688A+0QjWuuImLi7OpsAzFaNkTDxbnpwnenJwcAOdyFWPRkUq9lyorK5GYmNjPVM3W0HBPXV0d2tra4ODggICAACgUCqvsLfrCcRwefPBBfPvttzh48OCIGpmE4F//+hdeeuklNDQ0ID4+Hm+++SbS0tJGZd/2iN2IvTGEEFRVVfHC//vvv8PV1RXR0dF4+eWXkZCQILjAaTQaXthaWlr6NSpRA62Ojg6zZrQKzVjZE/ftcDYYDJDJZJg+ffqwjW62gBCCsrIy1NfXIykpaUzKbYFzHeNZWVkIDw+Hm5sbnwvR6XQm1T2WLk4MBgM2btyIH3/8EYcOHRo1b5kdO3Zg3bp12LZtG9LT0/Haa69h586dKCkpGbMelvMduxR7Y3bv3o3rrrsOf/nLX3hXzrCwML6yJzk5WfCyNprApMLm4OAAQgikUumYhivG2p4YOJeAzMjIgKurK5ycnNDc3AytVssnMEejnr/vwI+x6IoF/qz8mTZtGkKMhooYh8Oam5vR2dkJd3d3/jsaaVmwwWDAfffdh0OHDuHgwYOYPEpzmYFzfjapqal46623AJy7uwgJCcHdd9+NRx55ZNSOw56wa7H//fffsWTJEmzfvh2XX345gHPllt9++y327NmD7777Du7u7rxZ25w5cwQPJ3R1dSEzMxMSiQQGg4G3bqAJ3tFY0Y4He2Jg4K5YY2FTKpXo6uoaMs5vLcY+8GN54aWNYyMZTq7RaEyauWQyGX9h9Pb2HnCxYjAYcM899+DIkSM4ePAgPwNhNKDDdb788kusXr2af/z6669He3s7vv7661E7FnvCrsWeNgoNduuqVqtx4MAB7NmzB/v27ePN2latWoUFCxZY7VVOK26Cg4MxdepUAOcEr6mpCU1NTdBoNANaNwiJsT1xYmLimK1iR9oVO1Sc39rhI9QeWKvVIikpacwmGimVSuTm5lrUOGYwGPjqHqVSCb1ez1c/+fj4QC6Xw2AwYMOGDfjtt99w8ODBUZ/NW1dXh6CgIBw9ehSzZs3iH3/44Ydx5MgRHD9+fFSPx16wa7E3B2Oztq+//hpKpRILFy7EypUrTczaRspwFTe0MoMKP3WipHF+IYZiGNsTj1XDFmB5V2zfOL819fzUJhkYu4QwcC5nkp+fj5kzZ/Ij9SzF2M20ubkZ7733HnJzc6FQKHDmzBn8+uuvY2I3wcR+bGBibwHU0pYKf0lJCebPn4+VK1dixYoV8Pf3H1T4La24UavVfGVPW1sbXF1d4efnxw9lMXdFOx7siQHhumIHGlU50jg/NROTyWRjZlEM/HnRi4uLs0nO5MyZM3j44YeRmZmJjo4OBAYG8iP9RrMjmYVxxgYm9lZCqzZ27dqFr7/+GidPnkRqaipf0mls1qZSqVBWVoauri6rKm5oSV5f6wY/P78R3WGMB3ti44HcQnfFDhXn71v2qlarTS56ozUkvi+1tbUoKSmxWS2/TqfDbbfdhpycHBw8eBDe3t44dOgQvvnmG7zyyiujPj4xPT0daWlpePPNNwGcu1iHhoZiw4YNLEFrI5jYCwghBHV1dSZmbVFRUVixYgXmzJmDTZs24eKLL8Yzzzwj2AAFat1Ab9WpdYOfn9+Aybnm5mbk5uaO6WD00e6KHSzO7+bmhtLSUn4Qzlh8F8CfTVsJCQk2cTPV6XS4+eabUVhYiIMHD46ZgZwxO3bswPXXX49///vfSEtLw2uvvYYvvvgCxcXFVoevGAPDxN5GEELQ1taGffv24aOPPsIvv/yCqVOn4uKLL8Zll12G9PR0wcMFA1kTUOsGhUKBxsZGFBcXIyYmZszGsxnPaR2p146Q0Dh/XV0dH+cPCAjgL46jHcKprKxERUWFzZq2dDodbrzxRhQXF+PQoUPjaizfW2+9xTdVJSQk4I033uBHDDKEx+Zir9FokJ6ejpycHGRlZZkMP8jNzcVdd92FkydPwtfXF3fffTcefvhhk/fv3LkTTzzxBCorKzFt2jS88MILWLZsmS0PWVAOHz6Myy+/HDfffDPS09Oxd+9e7N+/HzKZjDdrE6pj1xhj64ampiaoVCqIRCKEhIQgPDx8TEazjZckKG1UCgsLg6enp4kNsa2rn4yhltFJSUlmW3OMBK1WixtuuAGnT5/GwYMH2YrZzrG52N97770oKyvDd999ZyL2nZ2diIyMxMKFC/Hoo48iLy8PN910E1577TV+evzRo0cxb948bNmyBStWrMCnn36KF154AZmZmZg5c6YtD1sQOI5Deno61q9fj5tuuol/XKfT4fDhw7xZm0qlwqJFi7Bq1SosWrRI0O5ZGjJpbm5GYGAg2tvb+SYcGucfjXJLOivWyckJsbGxY5YEpSWeQzUqDRfntxZjF8/k5GSbdOdqNBpcf/31qKysxIEDB1hXKsO2Yv/dd99h48aN+OqrrxATE2Mi9u+88w7+/ve/o6GhgV9BPfLII9izZw+Ki4sBAH/729+gUqmwf/9+fpsXXHABEhISsG3bNlsdtqDodLohV7AGg8HErO3s2bO45JJLsHLlygHN2sxhMHtiat3Q1NSE1tZWfpSen5+f2d7qI2EsZsUOBLUojo6OHjZubat6fuMGtuTkZJvYYmg0Glx33XWoqanBTz/9NGbd0Izxhc3EvrGxEcnJydizZw8UCgUiIiJMxH7dunXo7OzEnj17+Pf8/PPPuOSSS9Da2govLy+EhoZi48aNuO+++/jXPPnkk9izZw9vknU+Qc3aaGVPbm4uZs+ezVf2BAcHj1hkRmpP3Ne6QSqV8sLv6elptTCPh1mxwLna7uLiYousIGicn4q/pfX8hBAUFxejubnZZjYMarUa1157LRoaGvDjjz+O2ZAXxvjDJtN3CSG44YYbcMcddyAlJQWVlZX9XtPQ0NCvRZvGFBsaGuDl5YWGhoZ+cUZ/f380NDTY4rDHHJFIhJkzZ2LmzJl8noKu+B999FHExcXx83eHKpk0x56YOikGBASA4zi0traiqakJeXl5IISYePObG3qhlT/mTHWyBbSW39JqFwcHB/j7+8Pf39+knr+kpISP81PxHyzOTwjh7bNTUlJsUurY29uLtWvXorm5GT/99NOYuaYyxidmif0jjzyCF154YcjXFBUV4ccff0RXVxceffRRqw7OnhGJRIiIiMDGjRtx//33o6mpCfv27cPu3buxZcsWhIeH82ZtSUlJvKDn5OSgtbXVIntiOiBboVCAEMJbN5SWlpokL319fYdNro6HWbHUDuPs2bNITk4WpJZfLBbD29sb3t7eiIyM5Luca2pqUFRUNGCcnzqadnZ2IiUlxSYVSL29vVizZg3a2trw448/jslAesb4xiyxf+CBB3DDDTcM+ZrJkyfj0KFDOHbsWL+Kj5SUFKxduxbbt29HQEAAGhsbTZ6nf6flYYO9ZjyVj40GIpEI/v7+uOWWW3DLLbego6ODN2tbuXIlb9bm5eWF1157DV9++SXvtWPNPj09PeHp6Ylp06bxolZdXY3CwkJ4eXnx4Z6+4kXdMxMSEsZsdWkcG09JSbFJbFwkEsHV1RWurq6YPHky1Go1HxI7ffo0nJ2doVAo0NnZCa1Wi5SUFJtUQfX09ODqq69GV1cXfvzxR3h5eQm+D8bExyYx++rqanR2dvJ/r6urw+LFi/Hll18iPT0dwcHBfIK2sbGRXyU+9thj2LVrl0mCtqenB/v27eO3NXv2bMTFxU2YBK2t6e3txYEDB/Dcc88hIyMDM2bMQHx8PFauXCmIWdtg+6QJ3vb2dt66wdfXF/X19airqxvTWbG0AqmtrQ1JSUljYu6m1+uhVCpRVlYGjUZjkgsRsp5fpVLhb3/7G3p7e/Hdd9/ZpFa/srISzz77LA4dOoSGhgZMmjQJ1157Lf7+97/zYavKysoBnTOPHTuGCy64gP/7RC+lnsjYpCwiNDSUjz3PnDkTkZGRAIApU6bwAzGuueYayGQy3HzzzSgoKMCOHTvw+uuvY+PGjfx27r33Xnz//fd45ZVXUFxcjKeeegqnTp3Chg0bUFlZiZtvvhkRERFwcnLClClT8OSTT0Kr1ZocS25uLi688EI4OjoiJCQEL774Yr/j3blzJ6KiouDo6IjY2Fh8++23tvhabIJMJsPBgwdRWVmJ3377DW+88Qa8vb2xadMmhIWFYe3atfj888/R3t4Ooa7rTk5OCA0NRUpKCubNm4fQ0FB0dnbi+PHjqK6uhq+vLwghgu3PHDiOQ15eHjo6OpCSkjJmLp4ikQh1dXVwdHTEvHnzEBcXBwcHB5SUlODw4cPIzs5GbW1tv/PVHFQqFa688kpoNBp8//33NpukVVxcDI7j8O9//xsFBQV49dVXsW3bNjz22GP9XnvgwAHU19fzf5KTk/nnjh49ijVr1uDmm29GVlYWVq9ejdWrVyM/P98mx80wZVQ6aOlVf6imKoVCgbvvvhubNm0yee/OnTvx+OOP8yuBF198EcuWLcP333+PHTt2YM2aNZg6dSry8/Nx66234rrrrsPLL78MwD5q+evr67FmzRq8//77JsMnqFkbrewpKyvDvHnzRmTWZi60K7a3txehoaF8ApNWrQxm3SA01KJYp9MhMTFxzFw89Xo9srOzQQhBYmKiSSWUsZupNfX83d3duPLKK0EIwTfffGOTpqyheOmll/DOO+/gzJkzAAb/jRtzPpRST2TOK7uEviegvdTyDweNX9MxjKdOnUJaWhpf0hkREWGx8A/WFdvXuoH6qtPu1MFKQS1Fp9MhKysLYrEYCQkJgm/f3OOQSCRISEgYNlxD4/y0nt/JyWnYev6uri5cccUVkEgk2L9//5iMTHz88cfx/fff49SpUwD+FPuQkBCo1WpERkbi4YcfxqpVq/j32Fsp9XhjbLpbbERHR4dJFcKxY8cwb948kxXe4sWLUVJSgra2Nv41CxcuNNnO4sWLcezYsdE56FFAJBJh+vTpeOSRR3Ds2DFUVlbimmuuwcGDB5GUlIRZs2bhueeeQ15eHjiOG/F21Wo1Tp48yY9TNK7QoVUrUVFRmDt3Ll9XfubMGRw+fBiZmZmoqamBRqOx+vNpNBqcOnUKUqm030p6NNFqtcjIyIBUKh2R0AOAo6MjgoODkZiYiPnz52PKlCnQaDTIzs7GL7/8goKCAjQ1NUGv1wM4d7d62WWXwcHBAd98882YCP3p06fx5ptv4vbbb+cfc3V1xSuvvIKdO3fim2++wdy5c7F69Wrs3buXf429lVKPN8bmV2ED6AlIQzgAq+UfCJFIhODgYGzYsAF33XUXb9a2Z88evP766/D39+dLOocyazOnK1YkEsHd3R3u7u6YOnUqVCoVlEol3+hkzZhB6svv7u6OmJiYMevOpULv7OyM2NhYi45jsHr+0tJSPPHEE5BKpejp6YGzszP2799vdYXRSEupo6Ki+L/X1tZiyZIluOqqq3DrrbfyjysUCpN8W2pqKurq6vDSSy+ZrO4ZY8e4E3shT0DG0IhEInh7e+P666/H9ddfD5VKhe+//x579uzBX//6V8hkMn7+7rx58/iywVOnTqGjowNhYWFm1/IDgIuLC1xcXBAeHm5i3XD69GmzrBvoBUehUCAqKmrMunNt4Ynft57/qaeewnPPPYeqqip0dHRgyZIlWLVqFR544AGLK3tGWkpNqaurw8UXX4zZs2fj3XffHXb76enp+Omnn/i/s1LqsWXcib2QJyCr5TcPFxcXXHHFFbjiiiug1Wp5s7Y777wTKpUKixcvRkREBN544w288847WLBggdX7lMvlCA4ORnBwMHQ6He/NT8Myg1k3dHZ2IjMzE8HBwRZdcISit7cXGRkZfLeyLY6jo6MD//jHP+Dl5YWamhq0t7dj3759fG7AUmhuYCTU1tbi4osvRnJyMj744IMRXdCys7NNGupmzZqFgwcPmsTsf/rpJ5PRhAzbMaETtMYn4Mcff9zvxGe1/MJAzdo2b96M77//HlFRUYiIiMCKFSuwfPlyeHt7Cy5yHMeZ+NEQQnhxkkgkyM3NRURExKgPyzamp6cHGRkZNr2zaGtrw6pVq+Dr64vdu3eP+kQp4Nzv7KKLLkJYWBi2b99u8juji6Lt27dDJpMhMTERALBr1y488cQT+M9//oMbb7wRwLnKt/nz52Pr1q1Yvnw5Pv/8czz//PMTpvJtojNhE7T0BAwNDcXLL78MpVKJhoYGk1i7tbX8A/Gvf/0L4eHhcHR0RHp6Ok6cOGHzzzrWSCQS/PHHH/j111/x7bff4vPPP0dqaireffddTJ48GcuWLcM777yDmpoawWrradnmjBkzMG/ePL7Sp6ioCJmZmXBycoJMJoNOpxNkf+aiUqlw6tQp+Pn52UzoW1pasHLlSgQEBGDPnj1jIvTAudU39cQPDg5GYGAg/8eYZ599FsnJyUhPT8fXX3+NHTt28EIPnFtEffrpp3j33XcRHx+PL7/8Env27GFCP0pM2JX9hx9+aHIiGWP8kayp5e/Ljh07sG7dOmzbtg3p6el47bXXsHPnTpSUlJzXfuFqtRorVqzA1q1bkZKSwj9OCDExa/v999+RkJDAl3QKPd+2sbEReXl5mDp1KjiOQ1NTE7q7u4e0brAF3d3dyMjIwKRJk2zm5NnS0oIVK1YgNDQUX3755ZgMm2GcX0xYsR8L0tPTkZqairfeegvAuVBDSEgI7r77brsfkkwIQWNjI/bu3Ys9e/bg0KFDCA8Px8qVK7Fq1SokJiZalbikA7n7WhT3tW5wc3PjrRtcXFwEF2KaKwgNDbWqP2EompubsWLFCkREROCLL75gQs8QBCb2I0Sr1cLZ2RlffvklVq9ezT9+/fXXo729HV9//fXYHdw4pKOjA9988w327NnDt/LTyp7Zs2ebNZKwqqoKZ86cQUJCwpAmX1qtljcia2lpgaOjIy/81gwcMf5MmZmZNs0VNDU1YeXKlZg6dSp27NgxZl3AjPMPJvYjpK6uDkFBQTh69KhJ9cDDDz+MI0eO4Pjx42N4dOMbata2Z88e7Nu3DxzHYdmyZVixYsWQZm3G4/vMndNqMBj4yh5q3UCF3xLrhra2NmRnZ2PKlCk28+ZvbGzEihUrEBUVhc8++4wJPUNQxl3pJeP8w8nJiY/j6/V6/Pbbb9i1axcefvhhtLS0YOHChVi1ahWWLFkCd3d3iEQiGAwG/P777wDONeiYOwNWIpHwM3Y5jkNbWxuUSiUKCwthMBhMhrIM13FL59ZGRkbyRn5C09DQgOXLlyM2NhaffPLJmA1jZ5y/sJX9CGFhHOHhOA6ZmZm8Z8/p06cxf/58LFu2DN999x0aGhpw8OBBQZ0rCSHo7Ozk4/y9vb3w9vbmyzr7xseVSiXy8vIQFRWFSZMmCXYcxjQ0NGDZsmVISEjARx99xISeYROY2JtBeno60tLS8OabbwI4J1ahoaHYsGGD3SdorYWate3YsQOvvfYaAGDmzJlYunSp1WZtQ0GtG5qamtDZ2Wli3dDd3Y28vDzExMTYrMmuvr4eS5cuRWpqKrZv3z5mvj6M858JW2c/FmzcuBHvvfcetm/fjqKiIqxfvx4qlWrQElBjtmzZgtTUVL5aZPXq1SgpKTF5jVqtxl133QUfHx+4urriiiuu6NfdW11djeXLl8PZ2Rl+fn546KGHeJOsiYxIJEJQUBCOHDmC6dOn48iRI7jqqqtw4MAB3qxt8+bNZpu1DQe1bUhLS8OFF16IgIAAtLa24ujRo8jJyYGvry+cnZ1t4s1PbT7S09NtKvTh4eEQiUQmf7Zu3WrymvN97gMDAGGYxZtvvklCQ0OJTCYjaWlp5I8//hjR+xYvXkw++OADkp+fT7Kzs8myZctIaGgo6e7u5l9zxx13kJCQEHLw4EFy6tQpcsEFF5DZs2fzz+v1ejJz5kyycOFCkpWVRb799luiUCjIo48+KvjnHAv+7//+jyxcuJB0dXXxj3EcR5qbm8kHH3xALr30UuLs7EwmT55M7rnnHnLgwAHS2dlJVCqVoH/KysrI3r17SVZWFjl27BjZt28f+f7770lmZiY5e/Ys6erqsnofxcXFZPLkyWTdunVEp9PZ9HsNCwsjzzzzDKmvr+f/GJ93HR0dxN/fn6xdu5bk5+eTzz77jDg5OZF///vf/Gt+//13IpFIyIsvvkgKCwvJ448/TqRSKcnLy7PpsTOEg4n9GNHU1EQAkCNHjhBCCGlvbydSqZTs3LmTf01RUREBQI4dO0YIIeTbb78lYrGYNDQ08K955513iLu7O9FoNKP7AWzEcMLX1dVFdu7cSdauXUu8vLxIQEAAuemmm8iePXtIa2ur1SJcUlJC9u3bR86ePcs/1tnZSSorK8nJkyfJN998Q7755hty4sQJUlFRYdHFpqioiERERJAbb7yR6PV6m3+nYWFh5NVXXx30+bfffpt4eXmZnEObNm0i06dP5//+17/+lSxfvtzkfenp6eT2228X/HgZtoGFccaIjo4OAOD99zMyMqDT6Uy89aOiohAaGsp76x87dgyxsbEmlsyLFy9GZ2cnCgoKRvHobcdwoQxXV1dceeWV+Pjjj9HQ0IDt27dDKpVi/fr1iIiIwE033YTdu3eju7vb7H1XV1ejrKwMSUlJJnMRJBIJb90wf/58xMfHQyqVorS0FIcPH0ZOTg7q6+tHZN1QWVmJJUuWYMGCBXjvvfcEm0U7HFu3boWPjw8SExPx0ksvmYT+2NwH+4Blg8YAjuNw3333Yc6cObwvCJ2m1XeOqLG3/mDe+/Q5e0Mmk2HRokVYtGgR/vWvf+GPP/7A7t278fTTT+PWW2/FJZdcgpUrV2LZsmXDmrVVVFSgsrISSUlJQw5KF4lE8PLygpeXF6ZNm4bu7m40NTWhqqoKBQUF8PLy4uv5+1o3VFRUYNmyZViyZAnefvvtURP6e+65h7+AHT16FI8++ijq6+vxz3/+EwCb+2AvMLEfA+666y7k5+fjt99+G+tDOW+QSCSYM2cO5syZgxdffBEFBQX46quvsG3bNmzYsAFz5szha/2DgoJ44ec4DqWlpWhoaEBKSopZk59EIhHc3Nzg5uaGKVOm8NYNjY2NKCkpgZubGzo6OqBQKODp6Ylly5Zh2bJlePvtt632vDdn7oOx8V9cXBxkMhluv/12bNmyhVkx2BFM7EeZDRs2YP/+/fjll19MGnQCAgKg1WrR3t5usro39tYPCAjo57LZ15+fcc4xMzY2FrGxsXjyySdRUVHBm7Vt2rQJiYmJWLlyJZYvX4633noLNTU1+OSTT6ye/OTk5ITQ0FCEhoZCq9VCqVRi586d+O9//wtnZ2dERETg+uuvF+Qzmjv3wZj09HTo9XpUVlZi+vTpbO6DvTDWSQN7geM4ctddd5FJkyaR0tLSfs/TBO2XX37JP1ZcXDxggraxsZF/zb///W/i7u5O1Gq17T/EBIfjOFJfX0+2bdtGFi9eTBwdHYmnpydZv349+eWXXwSpsun7Jzs7m4SFhZFVq1aRa6+9lnh6epLAwEBSXFw8Zt/Dxx9/TMRiMWltbSWE/Jmg1Wq1/GseffTRfgnaFStWmGxn1qxZLEE7gWBiP0qsX7+eeHh4kMOHD5uUwPX09PCvueOOO0hoaCg5dOgQOXXqFJk1axaZNWsW/zwtvVy0aBHJzs4m33//PfH19R209HLLli0EALn33nv5x3p7e8mdd95JvL29iYuLC7n88stNqnsIIaSqqoosW7aMODk5EV9fX/Lggw/avDxwNDEYDOTWW28loaGh5NVXXyVXXXUVcXNzIyEhIWT9+vXku+++Ix0dHVYLfWZmJgkMDCT33XcfMRgMhBBCtFot+emnn0yE1ZYcPXqUvPrqqyQ7O5uUl5eTjz/+mPj6+pJ169bxr2lvbyf+/v7kuuuuI/n5+eTzzz8nzs7O/UovHRwcyMsvv0yKiorIk08+yUovJxhM7EcJAAP++eCDD/jXUCH28vIizs7O5LLLLiP19fUm26msrCRLly4lTk5ORKFQkAceeGBAIT5x4gQJDw8ncXFxJmJv77X8hBDyyiuvkGnTppHq6mr+sZ6eHvL111+TG2+8kSgUCuLj40Ouu+468sUXX5Dm5mazhf7UqVMkICCAPPDAA7zQjwUZGRkkPT2deHh4EEdHRxIdHU2ef/75fneCOTk5ZO7cuUQul5OgoCCydevWftv64osvSGRkJJHJZCQmJoZ88803o/UxGALAxP48pKuri0ybNo389NNPZP78+bzYs1r+c6hUqn4XUWN0Oh35+eefyd13301CQ0OJq6srueyyy8j7779P6urqSHd395BCf/LkSeLn50ceeuihMRV6BsMYVmd/HnLXXXdh+fLl/eqiWS3/OZydnYdMLDo4OOCiiy7CG2+8gYqKChw6dAhRUVF4+eWXER4ejssuuwzvv/8+Ghsb+9koFBQUYNmyZbjpppuwdetWq6tuGAyhYNU45xmff/45MjMzcfLkyX7PsVp+8xGLxUhNTUVqaio2b96MkpIS7Nq1Cx999BHuu+8+pKenY8WKFVi1ahVUKhWWL1+O22+/Hc888wwTesa4gp2N5xFnz57Fvffei08++WRUZrHaGyKRCFFRUXjsscfwxx9/oKKiAldffTUOHDiA+Ph4zJ49G7fccgueffZZJvSMcQc7I88jMjIy0NTUhKSkJDg4OMDBwQFHjhzBG2+8AQcHB/j7+/O1/Mb0reUfruaacU746fzhAwcOoL6+Hps2bcLzzz9vEytmBsNamNifRyxYsAB5eXnIzs7m/6SkpGDt2rX8/0ulUhw8eJB/T0lJCaqrq/lRi7NmzUJeXh6ampr41/z0009wd3fHjBkzRv0zTQREIhF8fX2xefNmJvSMcQuL2Z9HuLm58V47FBcXF/j4+PCP33zzzdi4cSO8vb3h7u6Ou+++G7NmzcIFF1wAAFi0aBFmzJiB6667Di+++CIaGhrw+OOP46677mKt9QzGBIat7O2MV199FStWrMAVV1yBefPmISAgALt27eKfl0gk2L9/PyQSCWbNmoVrr70W69atwzPPPGOyndraWlx77bXw8fGBk5MTYmNjcerUKf55Qgj+8Y9/IDAwEE5OTli4cCHKyspMttHa2oq1a9fC3d0dnp6euPnmmy1yq2QwGCNgrGs/GROP1tZWEhYWRm644QZy/PhxcubMGfLDDz+Q06dP86/ZunUr8fDwIHv27CE5OTlk1apVJCIigvT29vKvWbJkCYmPjyd//PEH+fXXX8nUqVPJmjVrxuIjjTt+/vnnQRvxTpw4QQghpKKiYsDnac8E5YsvviDTp08ncrmczJw5kzVD2SlM7Blms2nTJjJ37txBn+c4jgQEBJCXXnqJf6y9vZ3I5XLy2WefEUIIKSwsJADIyZMn+dd89913RCQSkdraWtsd/ARBo9GY2GrU19eTW265hURERBCO4wghf4r9gQMHTF5nbMXAJkwxKCyMwzCbvXv3IiUlBVdddRX8/PyQmJiI9957j3++oqICDQ0NJs1bHh4eSE9PN2ne8vT0REpKCv+ahQsXQiwW4/jx46P3YcYpMpkMAQEB/B8fHx98/fXXuPHGG/slgX18fExeK5VK+edef/11LFmyBA899BCio6Px7LPPIikpCW+99dZofyTGGMPEnmE2Z86cwTvvvINp06bhhx9+wPr163HPPfdg+/btAP5svhpq2EVDQwP8/PxMnndwcIC3t7ddNm8Nx969e9HS0jLgcPtVq1bBz88Pc+fOxd69e02eYxOmGBRWjcMwG47jkJKSgueffx4AkJiYiPz8fGzbtk0wv3aGKf/973+xePFikxkIrq6ueOWVVzBnzhyIxWJ89dVXWL16Nfbs2YNVq1YBGLwjml1Q7Q+2smeYTWBgYL+a++joaFRXVwP4s/lqqGEXAQEBJrX8AKDX69Ha2npeN2898sgjEIlEQ/4pLi42eU9NTQ1++OEH3HzzzSaPKxQKbNy4Eenp6UhNTcXWrVtx7bXX4qWXXhrNj8SYILCVPcNs5syZg5KSEpPHSktLERYWBgCIiIhAQEAADh48iISEBABAZ2cnjh8/jvXr1wM417zV3t6OjIwMJCcnAwAOHToEjuOQnp4+eh9mlLFkwtQHH3wAHx8ffrU+FOnp6fjpp5/4v7MJUwyesc4QMyYeJ06cIA4ODmTz5s2krKyMfPLJJ8TZ2Zl8/PHH/Gu2bt1KPD09yddff01yc3PJpZdeOmDpZWJiIjl+/Dj57bffyLRp00xKL/V6PXn88cdJeHg4cXR0JJMnTybPPPMMX41CyLnKnyeeeIIEBAQQR0dHsmDBgn6TwFpaWsg111xD3NzciIeHB7nppptIV1eXDb8h4eA4jkRERJAHHnhgRK+/5ZZbSGJiIv93NmGKQWFiz7CIffv2kZkzZxK5XE6ioqLIu+++a/I8FWF/f38il8vJggULSElJiclrWlpayJo1a4irqytxd3cnN954o4kIb968mfj4+JD9+/eTiooKsnPnTuLq6kpef/11/jXnez3/gQMHCABSVFTU77kPP/yQfPrpp6SoqIgUFRWRzZs3E7FYTN5//33+NWzCFIPCxJ4xblm+fDm56aabTB67/PLLydq1awkh9lHPv2bNGpNJYsZ8+OGHJDo6mjg7OxN3d3eSlpZmMpiGwiZMMQhhYs8Yx2zevJmEhYXxdwTZ2dnEz8+PDxeVl5cTACQrK8vkffPmzSP33HMPIYSQ//73v8TT09PkeZ1ORyQSCdm1a5ftPwSDMU5gCVrGuOWRRx5BZ2cnoqKiIJFIYDAYsHnzZqxduxYAq+dnMMyBiT1j3PLFF1/gk08+waeffoqYmBhkZ2fjvvvuw6RJk1g9P4NhJkzsGeOWhx56CI888giuvvpqAEBsbCyqqqqwZcsWXH/99Sb1/IGBgfz7Ghsb+ZJPe63nZzD6wpqqGOOWnp6efuP9JBIJOI4DYFrPT6H1/MbDWGg9P8Ue6vkZjL6wlT1j3LJy5Ups3rwZoaGhiImJQVZWFv75z3/ipptuAnBuQtR9992H5557DtOmTUNERASeeOIJTJo0CatXrwZwrrN3yZIluPXWW7Ft2zbodDps2LABV199NSZNmjSGn47BGGXGOkPMYAxGZ2cnuffee0loaCjfVPX3v/+daDQa/jVC1PMzGPaAiBBCxvqCw2AwGAzbwmL2DAaDYQcwsWcwGAw7gIk9g8Fg2AFM7BkMBsMOYGLPYDAYdgATewaDwbADmNgzGAyGHcDEnsFgMOwAJvYMBoNhBzCxZzAYDDuAiT2DwWDYAUzsGQwGww5gYs9gMBh2ABN7BoPBsAOY2DMYDIYdwMSewWAw7AAm9gwGg2EHMLFnMBgMO4CJPYPBYNgBTOwZDAbDDmBiz2AwGHYAE3sGg8GwA5jYMxgMhh3AxJ7BYDDsACb2DAaDYQcwsWcwGAw7gIk9g8Fg2AFM7BkMBsMOYGLPYDAYdgATewaDwbADmNgzGAyGHcDEnsFgMOwAJvYMBoNhBzCxZzAYDDuAiT2DwWDYAUzsGQwGww5gYs9gMBh2ABN7BoPBsAOY2DMYDIYdwMSewWAw7AAm9gwGg2EH/D/CGT6fBvF3fwAAAABJRU5ErkJggg==", + "text/plain": [ + "
" + ] + }, + "execution_count": 8, + "metadata": {}, + "output_type": "execute_result" + } + ], + "source": [ + "# Create a MoorPy system (this loads the moordyn outputs found in /_#.out, where is either Line or Rod and # is the corresponding number). File is required for MoorPy to know the mooring system parameters. \n", + "ms = moorpy.System(file=\"body.txt\", dirname=\"./\", rootname=\"body\", qs = 0, Fortran = False) # qs tells MoorPy it is loading a MoorDyn system, Fortran = False tells it to use the MoorDyn-C output format\n", + "\n", + "# Plot the results at t = 0 in red\n", + "ms.plot(color=\"red\", time = 0)" + ] + }, + { + "cell_type": "markdown", + "id": "a20bf7", + "metadata": { + "collapsed": false + }, + "source": [ + "# Closing Notes\n", + "\n", + "The process for running MoorDyn as described here is the same internals that OpenFAST and WEC-Sim both use when running coupled with MoorDyn. \n", + "At each timestep, the forces returned by MoorDyn are passed into these codes and used to determine the new position of the device which is \n", + "passed back to MoorDyn. In those codes, all you need to do is provide the MoorDyn input files and enable the relevant flags. The coupling is \n", + "all handled internally. \n", + "\n", + "MoorDyn is always looking for new projects to engage with. Couplings are underway with Chrono and Hydrochrono as well as numerous commercial codes. Any \n", + "new collaboration would be more than welcome!" + ] + } + ], + "metadata": { + "kernelspec": { + "display_name": "base", + "language": "python", + "name": "python3" + }, + "language_info": { + "codemirror_mode": { + "name": "ipython", + "version": 3 + }, + "file_extension": ".py", + "mimetype": "text/x-python", + "name": "python", + "nbconvert_exporter": "python", + "pygments_lexer": "ipython3", + "version": "3.11.8" + } + }, + "nbformat": 4, + "nbformat_minor": 4 +} diff --git a/example/PtfmMotions.dat b/example/PtfmMotions.dat new file mode 100644 index 00000000..9ba84fd9 --- /dev/null +++ b/example/PtfmMotions.dat @@ -0,0 +1,3 @@ +# Time Surge Sway Heave Roll Pitch Yaw +0.0 0 0 0 0 0 0 +0.5 0.25 0 0 0 0 0 \ No newline at end of file diff --git a/example/README.md b/example/README.md new file mode 100644 index 00000000..dc705539 --- /dev/null +++ b/example/README.md @@ -0,0 +1,11 @@ +This example directory contains instructions for common uses of MoorDyn, including OpenFAST, WEC-Sim, and running standalone. + +Before working with these examples, please look at the [MoorDyn documentation](https://moordyn.readthedocs.io/en/latest/drivers.html#python) for an explaination of the code and the different versions (MoorDyn-C and MoorDyn-F). After that, start out with working through the jupyter notebook (`MoorDyn_standalone_demo.ipynb`). This will walk through basic examples for running MoorDyn and visualzing outputs. Visualization is done with MoorPy, however Paraview can also be used as well as the tool [PyDatView](https://github.com/ebranlard/pyDatView). + +Further examples are the following: + +- `MHK_RM1_Floating`: This directory shows how to run MoorDyn-F with OpenFAST. +- `MoorDynF_example`: This directory shows how to use the MoorDyn-F driver from OpenFAST. +- `simpledemo.py`: This is the simplement example of how to run MoorDyn-C with a python script. +- `Running MoorDyn-F (OpenFAST).pdf`: This is a step-by-step list of iunstructions for running MoorDyn-F with OpenFAST. +- `Running WECSim with MoorDyn.pdf`: This is a step-by-step list of instructions for running MoorDyn-C with WECSim. \ No newline at end of file diff --git a/example/Running MoorDyn-F (OpenFAST).pdf b/example/Running MoorDyn-F (OpenFAST).pdf new file mode 100644 index 00000000..cc0ed975 Binary files /dev/null and b/example/Running MoorDyn-F (OpenFAST).pdf differ diff --git a/example/Running WECSim with MoorDyn.pdf b/example/Running WECSim with MoorDyn.pdf new file mode 100644 index 00000000..8410cc41 Binary files /dev/null and b/example/Running WECSim with MoorDyn.pdf differ diff --git a/example/body.txt b/example/body.txt new file mode 100644 index 00000000..a10173eb --- /dev/null +++ b/example/body.txt @@ -0,0 +1,42 @@ +--------------------- MoorDyn Input File ------------------------------------ +MoorDyn input file of the mooring system for OC3-Hywind +----------------------- LINE TYPES ------------------------------------------ +TypeName Diam Mass/m EA BA/-zeta EI Cd Ca CdAx CaAx +(name) (m) (kg/m) (N) (N-s/-) (N-m^2) (-) (-) (-) (-) +main 0.09 77.7066 384.243E6 -0.8 0 1.6 1.0 0.1 0.0 +----------------------- BODIES ------------------------------------------------------ +ID Attachment X0 Y0 Z0 r0 p0 y0 Mass CG* I* Volume CdA* Ca* +(#) (-) (m) (m) (m) (deg) (deg) (deg) (kg) (m) (kg-m^2) (m^3) (m^2) (-) +1 Coupled 0 0 -70 0 0 0 0 0 0 0 0 0 +---------------------- POINT PROPERTIES -------------------------------- +ID Type X Y Z Mass Volume CdA Ca +(#) (-) (m) (m) (m) (kg) (mˆ3) (m^2) (-) +1 Fixed 853.87 0 -320.0 0 0 0 0 +2 Fixed -426.94 739.47 -320.0 0 0 0 0 +3 Fixed -426.94 -739.47 -320.0 0 0 0 0 +4 Body1 5.2 0.0 0.0 0 0 0 0 +5 Body1 -2.6 4.5 0.0 0 0 0 0 +6 Body1 -2.6 -4.5 0.0 0 0 0 0 +---------------------- LINES ---------------------------------------- +ID LineType AttachA AttachB UnstrLen NumSegs LineOutputs +(#) (name) (#) (#) (m) (-) (-) +1 main 1 4 902.2 20 p +2 main 2 5 902.2 20 p +3 main 3 6 902.2 20 p +---------------------- OPTIONS ----------------------------------------- +2 writeLog Write a log file +0.002 dtM time step to use in mooring integration (s) +3.0e6 kBot bottom stiffness (Pa/m) +3.0e5 cBot bottom damping (Pa-s/m) +1025.0 WtrDnsty water density (kg/m^3) +320 WtrDpth water depth (m) +1.0 dtIC time interval for analyzing convergence during IC gen (s) +100.0 TmaxIC max time for ic gen (s) +4.0 CdScaleIC factor by which to scale drag coefficients during dynamic relaxation (-) +0.001 threshIC threshold for IC convergence (-) +1 disableOutTime +---------------------- OUTPUTS ----------------------------------------- +FairTen1 +FairTen2 +FairTen3 +------------------------- need this line -------------------------------------- diff --git a/example/jonkman_2010_3-1.png b/example/jonkman_2010_3-1.png new file mode 100644 index 00000000..1b27f8c5 Binary files /dev/null and b/example/jonkman_2010_3-1.png differ diff --git a/example/lines.txt b/example/lines.txt new file mode 100644 index 00000000..dc1c1943 --- /dev/null +++ b/example/lines.txt @@ -0,0 +1,38 @@ +--------------------- MoorDyn Input File ------------------------------------ +MoorDyn input file of the mooring system for OC3-Hywind +----------------------- LINE TYPES ------------------------------------------ +TypeName Diam Mass/m EA BA/-zeta EI Cd Ca CdAx CaAx +(name) (m) (kg/m) (N) (N-s/-) (N-m^2) (-) (-) (-) (-) +main 0.09 77.7066 384.243E6 -0.8 0 1.6 1.0 0.1 0.0 +---------------------- POINT PROPERTIES -------------------------------- +ID Type X Y Z Mass Volume CdA Ca +(#) (-) (m) (m) (m) (kg) (mˆ3) (m^2) (-) +1 Fixed 853.87 0 -320.0 0 0 0 0 +2 Fixed -426.94 739.47 -320.0 0 0 0 0 +3 Fixed -426.94 -739.47 -320.0 0 0 0 0 +4 Coupled 5.2 0.0 -70.0 0 0 0 0 +5 Coupled -2.6 4.5 -70.0 0 0 0 0 +6 Coupled -2.6 -4.5 -70.0 0 0 0 0 +---------------------- LINES ---------------------------------------- +ID LineType AttachA AttachB UnstrLen NumSegs LineOutputs +(#) (name) (#) (#) (m) (-) (-) +1 main 1 4 902.2 20 p +2 main 2 5 902.2 20 p +3 main 3 6 902.2 20 p +---------------------- OPTIONS ----------------------------------------- +2 writeLog Write a log file +0.002 dtM time step to use in mooring integration (s) +3.0e6 kBot bottom stiffness (Pa/m) +3.0e5 cBot bottom damping (Pa-s/m) +1025.0 WtrDnsty water density (kg/m^3) +320 WtrDpth water depth (m) +1.0 dtIC time interval for analyzing convergence during IC gen (s) +100.0 TmaxIC max time for ic gen (s) +4.0 CdScaleIC factor by which to scale drag coefficients during dynamic relaxation (-) +0.001 threshIC threshold for IC convergence (-) +1 disableOutTime +---------------------- OUTPUTS ----------------------------------------- +FairTen1 +FairTen2 +FairTen3 +------------------------- need this line -------------------------------------- \ No newline at end of file diff --git a/example/md_driver.dvr b/example/md_driver.dvr new file mode 100644 index 00000000..5020a479 --- /dev/null +++ b/example/md_driver.dvr @@ -0,0 +1,19 @@ +MoorDyn driver input file +another comment line +---------------------- ENVIRONMENTAL CONDITIONS ------------------------------- +9.80665 Gravity - Gravity (m/s^2) +1025.0 rhoW - Water density (kg/m^3) +10.0 WtrDpth - Water depth (m) +---------------------- MOORDYN ------------------------------------------------ +"../body.txt" MDInputFile - Primary MoorDyn input file name (quoted string) +"body" OutRootName - The name which prefixes all MoorDyn generated files (quoted string) +0.5 TMax - Number of time steps in the simulations (-) +0.5 dtC - TimeInterval for the simulation (sec) +0 InputsMode - MoorDyn coupled object inputs (0: all inputs are zero for every timestep (no coupled objects), 1: time-series inputs (coupled objects)) (switch) +"PtfmMotions.dat" InputsFile - Filename for the MoorDyn inputs file for when InputsMod = 1 (quoted string) +0 NumTurbines - Number of wind turbines (-) [>=1 to use FAST.Farm mode. 0 to use OpenFAST mode.] +---------------------- Initial Positions -------------------------------------- +ref_X ref_Y surge_init sway_init heave_init roll_init pitch_init yaw_init +(m) (m) (m) (m) (m) (rad) (rad) (rad) [followed by MAX(1,NumTurbines) rows of data] +0 0 0 0 0 0 0 0 +END of driver input file \ No newline at end of file diff --git a/example/simpledemo.py b/example/simpledemo.py new file mode 100644 index 00000000..d61fe2c3 --- /dev/null +++ b/example/simpledemo.py @@ -0,0 +1,31 @@ +import moordyn +import numpy as np + +''' +This is a very simple example of how to use the MoorDyn Python interface. Users need to provide a moordyn input file before running. +''' + +# Create the MoorDyn system from the input file +system = moordyn.Create("") + +# You can get the initial positions and velocities from the system itself using the MoorDyn-C API +body = moordyn.GetBody(system, 1) +state = moordyn.GetBodyState(body) # tuple with (x, xd) + +x = np.array(state[0]) # x, y, z, roll, pitch, yaw +xd = np.array(state[1]) # xdot, ydot, zdot, roll_dot, pitch_dot, yaw_dot + +# Setup the initial condition +moordyn.Init(system, x, xd) + +# Set the simulation time +t, dt = 0.0, 0.5 + +# Run the simulation for five timesteps +for i in range(5): + f = moordyn.Step(system, x, xd, t, dt) + t += dt + x += xd * dt # update the position + +# Alright, time to finish! +moordyn.Close(system) \ No newline at end of file