Added restart file for tutorials regression

Author: EvertBunschoten

incompressible_flow/Inc_Combustion/1__premixed_hydrogen/H2_burner.cfg

@@ -33,7 +33,7 @@ FLUID_MODEL= FLUID_FLAMELET
 
 % List the MLP files describing the respective architectures.
 INTERPOLATION_METHOD= MLP
-FILENAMES_INTERPOLATOR= (MLP_TD1_n.mlp, MLP_TD2.mlp, MLP_PD.mlp, MLP_SPV.mlp, MLP_PNO.mlp, MLP_null.mlp)
+FILENAMES_INTERPOLATOR= (MLP_TD1.mlp, MLP_TD2.mlp, MLP_PD.mlp, MLP_SPV.mlp, MLP_PNO.mlp, MLP_null.mlp)
 
 % FGM controlling variable names (must include mixture fraction for partial 
 % premixed cases)
@@ -61,7 +61,7 @@ SPARK_REACTION_RATES=(1000, 0, 0)
 
 CONV_NUM_METHOD_SPECIES= BOUNDED_SCALAR
 
-MUSCL_SPECIES= NO
+MUSCL_SPECIES= YES
 SLOPE_LIMITER_SPECIES= NONE
 TIME_DISCRE_SPECIES= EULER_IMPLICIT
 % SCALAR CLIPPING
@@ -71,14 +71,14 @@ SPECIES_CLIPPING_MAX= +4.6642374992370605e-01 +2.1569957500000000e+06 +1.4977467
 %
 % Inlet and initial condition corresponding to mixture at T=300K, eq ratio 0.5
 SPECIES_INIT=(-0.575, 2.227e3, 1.447e-2, 0)
-MARKER_INLET_SPECIES = (inlet, -0.575, 2.227e3, 1.447e-29, 0)
+MARKER_INLET_SPECIES = (inlet, -0.575, 2.227e3, 1.447e-2, 0)
 
 INC_INLET_TYPE= VELOCITY_INLET
 MARKER_INLET=(inlet, 300.0, 0.575,1,0,0)
 CFL_REDUCTION_SPECIES= 1.0
 
 MARKER_ISOTHERMAL=(burner_wall, 350, \
-                        cylinder_wall, 350)
+                        cylinder_wall, 400)
 MARKER_SPECIES_STRONG_BC=(burner_wall,cylinder_wall)
 MARKER_INTERNAL=(fluid)
 % ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
@@ -92,19 +92,18 @@ REF_AREA= 1.0
 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
 %
 
-%__ADJOINT__MARKER_SYM= (sides, mixing_edge)
 MARKER_SYM= (sides)
 INC_OUTLET_TYPE= PRESSURE_OUTLET
 INC_INLET_DAMPING = 0.05
 INC_OUTLET_DAMPING = 0.05
 MARKER_OUTLET= (outlet, 0.0)
-% MARKER_SPECIES_STRONG_BC = (CHT_INTERFACE_FLUID_VENTURI, CHT_INTERFACE_FLUID_BURNER)
+
 % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
 %
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
 CFL_NUMBER= 150
 CFL_ADAPT= NO
-ITER= 3000
+ITER= 5
 %
 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
 %
@@ -132,19 +131,14 @@ CONV_CAUCHY_ELEMS= 100
 CONV_CAUCHY_EPS= 1E-6
 SCREEN_OUTPUT = INNER_ITER RMS_VELOCITY-X RMS_PRESSURE RMS_ProgressVariable RMS_EnthalpyTot RMS_MixtureFraction
 HISTORY_OUTPUT = RMS_RES 
-VOLUME_OUTPUT = SOLUTION RESIDUAL SENSITIVITY LOOKUP TIMESTEP PRIMITIVE SOURCE
+VOLUME_OUTPUT = SOLUTION
 CONV_FIELD = RMS_PRESSURE, RMS_VELOCITY-Z, RMS_VELOCITY-Y, RMS_MixtureFraction
 WRT_ZONE_HIST= YES
 %
 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
 %
-RESTART_SOL=NO
+RESTART_SOL=YES
 OUTPUT_PRECISION= 16
 TABULAR_FORMAT = CSV
 MESH_FILENAME=H2_burner.su2
-OUTPUT_FILES=(RESTART_ASCII, PARAVIEW_MULTIBLOCK)
-WRT_PERFORMANCE = NO 
-READ_BINARY_RESTART=NO
-SCREEN_WRT_FREQ_INNER = 1
-SCREEN_WRT_FREQ_OUTER = 1
-OUTPUT_WRT_FREQ=20
+OUTPUT_FILES=(RESTART, PARAVIEW_MULTIBLOCK)

incompressible_flow/Inc_Combustion/1__premixed_hydrogen/H2_burner.geo

@@ -49,34 +49,49 @@ Curve Loop(1) = {1, 9, -10, 8, -7, -6, -5, -4, -3, -2};
 //+
 Plane Surface(1) = {1};
 //+
-Physical Curve("inlet", 11) = {1};
+//Physical Curve("inlet", 11) = {1};
 //+
-Physical Curve("outlet", 12) = {7};
+//Physical Curve("outlet", 12) = {7};
 //+
-Physical Curve("burner_wall", 13) = {3, 4, 5};
+//Physical Curve("burner_wall", 13) = {3, 4, 5};
 //+
-Physical Curve("cylinder_wall", 14) = {10};
+//Physical Curve("cylinder_wall", 14) = {10};
 //+
-Physical Curve("sides", 15) = {2, 9, 6, 8};
+//Physical Curve("sides", 15) = {2, 9, 6, 8};
 //+
-Physical Surface("fluid", 16) = {1};
+//Physical Surface("fluid", 16) = {1};
 //+
-Transfinite Curve {1, 7} = 40 Using Progression 1;
+Transfinite Curve {1, 7} = 30 Using Progression 1;
 //+
-Transfinite Curve {3, 5} = 40 Using Progression 1;
+Transfinite Curve {3, 5} = 30 Using Progression 1;
 //+
-Transfinite Curve {4} = 100 Using Progression 1;
+Transfinite Curve {4} = 80 Using Progression 1;
 //+
-Transfinite Curve {2} = 150 Using Progression 1;
+Transfinite Curve {2} = 100 Using Progression 1;
 //+
-Transfinite Curve {6} = 400 Using Progression 1;
+Transfinite Curve {6} = 300 Using Progression 1;
 //+
-Transfinite Curve {8} = 270 Using Progression 1;
+Transfinite Curve {8} = 200 Using Progression 1;
 //+
-Transfinite Curve {9} = 470 Using Progression 1;
+Transfinite Curve {9} = 350 Using Progression 1;
 //+
-Transfinite Curve {10} = 150 Using Progression 1;
+Transfinite Curve {10} = 100 Using Progression 1;
 
-Mesh 2;
+//Mesh 2;
 
-Save "H2_burner.su2";
+//Save "H2_burner.su2";//+
+Extrude {{1, 0, 0}, {0, -0.001, 0}, Pi/8} {
+  Surface{1}; Layers{10}; Recombine;
+}
+//+
+Physical Surface("inlet", 63) = {25};
+//+
+Physical Surface("outlet", 64) = {41};
+//+
+Physical Surface("sides", 65) = {62, 29, 61, 1, 45, 37};
+//+
+Physical Surface("burner_wall", 66) = {57, 53, 49};
+//+
+Physical Surface("cylinder_wall", 67) = {33};
+//+
+Physical Volume("fluid", 68) = {1};