adding test case using CONSTANT_CONDUCTIVITY model

TestCases/parallel_regression.py

@@ -392,6 +392,14 @@ def main():
     turb_flatplate_species.test_vals = [-4.243064, -0.634797, -1.706652, 1.231264, -3.266203, 9.000000, -6.632972, 5.000000, -6.985977, 10.000000, -6.007208, 0.996237, 0.996237]
     test_list.append(turb_flatplate_species)
 
+    # Flat plate (compressible) species transport using constant conductivity model
+    turb_flatplate_species           = TestCase('turb_flatplate_species_ConstConductivity')
+    turb_flatplate_species.cfg_dir   = "rans/flatplate"
+    turb_flatplate_species.cfg_file  = "turb_SA_flatplate_species_ConstConductivity.cfg"
+    turb_flatplate_species.test_iter = 20
+    turb_flatplate_species.test_vals = [-4.243064, -0.634797, -1.706652, 1.231264, -3.266203, 9.000000, -6.632972, 5.000000, -6.985977, 10.000000, -6.007208, 0.996237, 0.996237]
+    test_list.append(turb_flatplate_species)
+
     # Flat plate SST compressibility correction Wilcox
     turb_flatplate_CC_Wilcox = TestCase('turb_flatplate_CC_Wilcox')
     turb_flatplate_CC_Wilcox.cfg_dir   = "rans/flatplate"

TestCases/rans/flatplate/turb_SA_flatplate_species_ConstConductivity.cfg

@@ -0,0 +1,140 @@
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                              %
+% SU2 configuration file                                                       %
+% Case description: Turbulent flow over flat plate with zero pressure gradient %
+%                   using conductivity model CONSTANT_CONDUCTIVITY             %
+% Author: C. Morales Ubal                                                      %
+% Institution: Eindhoven University of Technology                              %
+% Date: 2025.02.22                                                             %
+% File Version 8.1.0 "Harrier"                                                 %
+%                                                                              %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
+%
+SOLVER= RANS
+KIND_TURB_MODEL= SA
+MATH_PROBLEM= DIRECT
+RESTART_SOL= NO
+
+% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
+%
+MACH_NUMBER= 0.2
+AOA= 0.0
+SIDESLIP_ANGLE= 0.0
+FREESTREAM_TEMPERATURE= 300.0
+REYNOLDS_NUMBER= 5000000.0
+REYNOLDS_LENGTH= 1.0
+
+% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
+%
+REF_ORIGIN_MOMENT_X = 0.25
+REF_ORIGIN_MOMENT_Y = 0.00
+REF_ORIGIN_MOMENT_Z = 0.00
+REF_LENGTH= 1.0
+REF_AREA= 2.0
+
+% -------------------- FLUID PROPERTIES ------------------------------------- %
+%
+FLUID_MODEL= IDEAL_GAS
+%
+MOLECULAR_WEIGHT= 28.960
+%
+SPECIFIC_HEAT_CP = 1009.39
+%
+CONDUCTIVITY_MODEL= CONSTANT_CONDUCTIVITY
+THERMAL_CONDUCTIVITY_CONSTANT= 0.0258 
+%
+PRANDTL_LAM= 0.72
+TURBULENT_CONDUCTIVITY_MODEL= CONSTANT_PRANDTL_TURB
+PRANDTL_TURB= 0.90
+%
+% --------------------------- VISCOSITY MODEL ---------------------------------%
+%
+VISCOSITY_MODEL= CONSTANT_VISCOSITY
+%
+MU_CONSTANT= 1.8551E-05 
+%
+% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
+%
+MARKER_HEATFLUX= ( wall, 0.0 )
+SPECIFIED_INLET_PROFILE= NO
+INLET_FILENAME= inlet.dat
+INC_INLET_TYPE=  VELOCITY_INLET
+MARKER_INLET= ( inlet, 302.4, 118309.784, 1.0, 0.0, 0.0 )
+MARKER_INLET_SPECIES= ( inlet, 1.0 )
+MARKER_OUTLET= ( outlet, 115056.0, farfield, 115056.0 )
+MARKER_SYM= ( symmetry )
+MARKER_PLOTTING= ( wall )
+MARKER_MONITORING= ( wall )
+
+% -------------------- SCALAR TRANSPORT ---------------------------------------%
+%
+KIND_SCALAR_MODEL= SPECIES_TRANSPORT
+DIFFUSIVITY_MODEL= CONSTANT_DIFFUSIVITY
+DIFFUSIVITY_CONSTANT= 0.001
+CONV_NUM_METHOD_SPECIES= SCALAR_UPWIND
+MUSCL_SPECIES= NO
+SLOPE_LIMITER_SPECIES = NONE
+TIME_DISCRE_SPECIES= EULER_IMPLICIT
+SPECIES_INIT= 1.0
+SPECIES_CLIPPING= YES
+SPECIES_CLIPPING_MIN= 0.0
+SPECIES_CLIPPING_MAX= 1.0
+
+% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
+%
+NUM_METHOD_GRAD= GREEN_GAUSS
+CFL_NUMBER= 10.0
+CFL_ADAPT= YES
+CFL_ADAPT_PARAM= ( 0.5, 2.0, 1.0, 1000.0 )
+ITER= 10000
+% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
+%
+LINEAR_SOLVER= FGMRES
+LINEAR_SOLVER_PREC= ILU
+LINEAR_SOLVER_ERROR= 1E-5 
+LINEAR_SOLVER_ITER= 5
+%
+% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
+%
+CONV_NUM_METHOD_FLOW= ROE
+MUSCL_FLOW= NO
+SLOPE_LIMITER_FLOW= NONE
+JST_SENSOR_COEFF= ( 0.5, 0.02 )
+TIME_DISCRE_FLOW= EULER_IMPLICIT
+
+% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
+%
+CONV_NUM_METHOD_TURB= SCALAR_UPWIND
+MUSCL_TURB= NO
+SLOPE_LIMITER_TURB= VENKATAKRISHNAN
+TIME_DISCRE_TURB= EULER_IMPLICIT
+
+% --------------------------- CONVERGENCE PARAMETERS --------------------------%
+CONV_RESIDUAL_MINVAL= -15
+CONV_STARTITER= 10
+CONV_CAUCHY_ELEMS= 100
+CONV_CAUCHY_EPS= 1E-6
+
+% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
+%
+MESH_FILENAME= mesh_flatplate_turb_137x97.su2
+SCREEN_OUTPUT= INNER_ITER WALL_TIME \
+               RMS_DENSITY RMS_MOMENTUM-X RMS_MOMENTUM-Y RMS_ENERGY RMS_TKE RMS_DISSIPATION RMS_SPECIES_0 \
+               LINSOL_ITER LINSOL_RESIDUAL \
+               LINSOL_ITER_TURB LINSOL_RESIDUAL_TURB \
+               LINSOL_ITER_SPECIES LINSOL_RESIDUAL_SPECIES \
+               SURFACE_SPECIES_0
+SCREEN_WRT_FREQ_INNER= 10
+HISTORY_OUTPUT= ITER RMS_RES LINSOL SPECIES_COEFF SPECIES_COEFF_SURF
+CONV_FILENAME= history
+MARKER_ANALYZE= outlet
+MARKER_ANALYZE_AVERAGE= AREA
+OUTPUT_FILES= RESTART_ASCII, PARAVIEW_MULTIBLOCK
+VOLUME_OUTPUT= RESIDUAL, PRIMITIVE
+OUTPUT_WRT_FREQ= 100
+READ_BINARY_RESTART= NO
+RESTART_FILENAME= restart
+SOLUTION_FILENAME= solution
+