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Added files for vandv case sandia jet for test cases
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‎.github/workflows/regression.yml‎

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uses: docker://ghcr.io/su2code/su2/test-su2:230704-1323
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with:
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# -t <Tutorials-branch> -c <Testcases-branch>
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args: -b ${{github.ref}} -t develop -c develop -s ${{matrix.testscript}}
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args: -b ${{github.ref}} -t develop -c feature_validation_sandia_jet -s ${{matrix.testscript}}
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- name: Cleanup
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uses: docker://ghcr.io/su2code/su2/test-su2:230704-1323
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with:

‎TestCases/vandv.py‎

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swbli_sst.test_vals = [-11.527743, -11.150388, -11.944923, -10.750834, -11.116769, -4.030059, 0.002339, -2.730391, -4.067274, 1.276300]
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test_list.append(swbli_sst)
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##########################
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### Incompressible RANS ###
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##########################
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# Sandia jet - sst-v2003m
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sandiajet_sst = TestCase('sandiajet_sst')
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sandiajet_sst.cfg_dir = "vandv/species_transport/sandia_jet"
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sandiajet_sst.cfg_file = "VALIDATION.cfg"
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sandiajet_sst.test_iter = 5
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sandiajet_sst.test_vals = [-11.527743, -11.150388, -11.944923, -10.750834, -11.116769, -4.030059]
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test_list.append(sandiajet_sst)
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#################
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### RUN TESTS ###
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#################

‎TestCases/vandv/species_transport/sandia_jet/VALIDATION.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: V&V Composition-dependent model Sandia's turbulent jet %
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% Author: S.J.H. Bosmans %
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% Institution: TU Eindhoven (TU/e) %
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% Date: 2023/05/04 %
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% File Version 7.5.0 "Blackbird" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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SOLVER= INC_RANS
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KIND_TURB_MODEL= SST
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SST_OPTIONS= V2003m
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RESTART_SOL= YES
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%
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% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
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%
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INC_DENSITY_MODEL= VARIABLE
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INC_DENSITY_INIT= 1.828
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%
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INC_VELOCITY_INIT= ( 53.0, 0.0, 0.0 )
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%
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INC_ENERGY_EQUATION= NO
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INC_TEMPERATURE_INIT= 294.0
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%
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INC_NONDIM= DIMENSIONAL
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%
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% -------------------- FLUID PROPERTIES ------------------------------------- %
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%
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FLUID_MODEL= FLUID_MIXTURE
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%
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MOLECULAR_WEIGHT= 44.097, 28.960
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THERMODYNAMIC_PRESSURE = 101325.0
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%
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SPECIFIC_HEAT_CP = 1680.0, 1009.39
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%
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CONDUCTIVITY_MODEL= CONSTANT_CONDUCTIVITY
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THERMAL_CONDUCTIVITY_CONSTANT= 0.0179, 0.0258
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%
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PRANDTL_LAM= 0.72, 0.72
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TURBULENT_CONDUCTIVITY_MODEL= CONSTANT_PRANDTL_TURB
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PRANDTL_TURB= 0.90, 0.90
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%
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% --------------------------- VISCOSITY MODEL ---------------------------------%
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%
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VISCOSITY_MODEL= CONSTANT_VISCOSITY
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%
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MU_CONSTANT= 8.04E-06, 1.8551E-05
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%
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MIXING_VISCOSITY_MODEL = WILKE
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%
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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MARKER_HEATFLUX= ( wall, 0.0 )
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AXISYMMETRIC= YES
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MARKER_SYM= ( symmetry )
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MARKER_EULER= ( top_wall )
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MARKER_INLET_TURBULENT= ( inlet_gas, 0.04, 5, inlet_air, 0.004, 1 )
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%
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INC_INLET_TYPE= VELOCITY_INLET VELOCITY_INLET
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SPECIFIED_INLET_PROFILE= NO
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%INLET_FILENAME= inlet_jet.dat
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%INLET_MATCHING_TOLERANCE= 1.2E-06
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%
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MARKER_INLET= ( inlet_gas, 294, 53.0, 1.0, 0.0 0.0, inlet_air, 294, 9.2, 1.0, 0.0, 0.0 )
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MARKER_INLET_SPECIES= ( inlet_gas, 1.0, inlet_air, 0.0 )
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%
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INC_OUTLET_TYPE= PRESSURE_OUTLET
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MARKER_OUTLET= ( outlet, 0.0 )
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%
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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%
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CFL_NUMBER= 200.0
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CFL_ADAPT= NO
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CFL_REDUCTION_SPECIES= 1.0
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CFL_REDUCTION_TURB= 0.5
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%
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ITER= 9999
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%
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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LINEAR_SOLVER= FGMRES
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LINEAR_SOLVER_PREC= ILU
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LINEAR_SOLVER_ERROR= 1E-5
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LINEAR_SOLVER_ITER= 5
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%
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= FDS
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MUSCL_FLOW= NO
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SLOPE_LIMITER_FLOW = NONE
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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%
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% -------------------- SCALAR TRANSPORT ---------------------------------------%
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%
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KIND_SCALAR_MODEL= SPECIES_TRANSPORT
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%
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DIFFUSIVITY_MODEL= UNITY_LEWIS
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%
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SCHMIDT_NUMBER_TURBULENT= 0.7
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%
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CONV_NUM_METHOD_SPECIES= BOUNDED_SCALAR
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MUSCL_SPECIES= NO
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SLOPE_LIMITER_SPECIES = NONE
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%
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TIME_DISCRE_SPECIES= EULER_IMPLICIT
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%
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SPECIES_INIT= 0.05
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SPECIES_CLIPPING= NO
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SPECIES_CLIPPING_MIN= 0.0
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SPECIES_CLIPPING_MAX= 1.0
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%
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% -------------------- TURBULENT TRANSPORT ---------------------------------------%
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%
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CONV_NUM_METHOD_TURB= BOUNDED_SCALAR
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MUSCL_TURB= NO
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%
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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CONV_FIELD= RMS_PRESSURE, RMS_VELOCITY-X, RMS_VELOCITY-Y, RMS_TKE, RMS_SPECIES
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CONV_RESIDUAL_MINVAL= -14.0
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CONV_CAUCHY_ELEMS= 100
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CONV_CAUCHY_EPS= 1E-6
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%
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= MESH_validation.su2
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%
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SCREEN_OUTPUT= INNER_ITER WALL_TIME RMS_RES LINSOL_ITER LINSOL_RESIDUAL LINSOL_ITER_TURB LINSOL_RESIDUAL_TURB LINSOL_ITER_SPECIES LINSOL_RESIDUAL_SPECIES SURFACE_SPECIES_VARIANCE SURFACE_TOTAL_PRESSURE
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SCREEN_WRT_FREQ_INNER= 10
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%
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HISTORY_OUTPUT= ITER RMS_RES LINSOL SPECIES_COEFF SPECIES_COEFF_SURF SURFACE_TOTAL_PRESSURE
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CONV_FILENAME= history
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MARKER_ANALYZE= inlet_gas,inlet_air, outlet
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MARKER_ANALYZE_AVERAGE= AREA
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%
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OUTPUT_FILES= RESTART_ASCII, PARAVIEW_MULTIBLOCK
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VOLUME_OUTPUT= RESIDUAL, PRIMITIVE
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OUTPUT_WRT_FREQ= 100
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%
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READ_BINARY_RESTART= NO
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RESTART_FILENAME= restart.csv
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SOLUTION_FILENAME= solution.csv
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%
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WRT_PERFORMANCE= YES
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OUTPUT_PRECISION= 16

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