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Adding V&V case compos. dep. model to test cases. #2100

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merged 4 commits into from
Aug 6, 2023
Merged

Adding V&V case compos. dep. model to test cases. #2100

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374a385
Added files for vandv case sandia jet for test cases
Aug 3, 2023
6e0db0d
Update .github/workflows/regression.yml
pcarruscag Aug 4, 2023
72230f9
Update TestCases/vandv.py
pcarruscag Aug 4, 2023
9587175
Merge branch 'develop' into feature_validation_sandia_jet
Cristopher-Morales Aug 4, 2023
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12 changes: 12 additions & 0 deletions TestCases/vandv.py
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Original file line number Diff line number Diff line change
Expand Up @@ -85,6 +85,18 @@ def main():
swbli_sst.test_vals = [-11.527743, -11.150388, -11.944923, -10.750834, -11.116769, -4.030059, 0.002339, -2.730391, -4.067274, 1.276300]
test_list.append(swbli_sst)

##########################
### Incompressible RANS ###
##########################

# Sandia jet - sst-v2003m
sandiajet_sst = TestCase('sandiajet_sst')
sandiajet_sst.cfg_dir = "vandv/species_transport/sandia_jet"
sandiajet_sst.cfg_file = "VALIDATION.cfg"
sandiajet_sst.test_iter = 5
sandiajet_sst.test_vals = [-16.249917, -13.835991, -14.303372, -13.276035, -10.074262, -14.027223, 5, -1.672359, 5, -4.938477, 5, -3.462217, 2.5859e-04, 2.8215e-32, 4.5010e-68, 2.5859e-04, 4.0474e+03, 3.9468e+03, 4.9170e+01, 5.1441e+01]
test_list.append(sandiajet_sst)

#################
### RUN TESTS ###
#################
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151 changes: 151 additions & 0 deletions TestCases/vandv/species_transport/sandia_jet/VALIDATION.cfg
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@@ -0,0 +1,151 @@
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
% SU2 configuration file %
% Case description: V&V Composition-dependent model Sandia's turbulent jet %
% Author: S.J.H. Bosmans %
% Institution: TU Eindhoven (TU/e) %
% Date: 2023/05/04 %
% File Version 7.5.0 "Blackbird" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
SOLVER= INC_RANS
KIND_TURB_MODEL= SST
SST_OPTIONS= V2003m
RESTART_SOL= YES
%
% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
%
INC_DENSITY_MODEL= VARIABLE
INC_DENSITY_INIT= 1.828
%
INC_VELOCITY_INIT= ( 53.0, 0.0, 0.0 )
%
INC_ENERGY_EQUATION= NO
INC_TEMPERATURE_INIT= 294.0
%
INC_NONDIM= DIMENSIONAL
%
% -------------------- FLUID PROPERTIES ------------------------------------- %
%
FLUID_MODEL= FLUID_MIXTURE
%
MOLECULAR_WEIGHT= 44.097, 28.960
THERMODYNAMIC_PRESSURE = 101325.0
%
SPECIFIC_HEAT_CP = 1680.0, 1009.39
%
CONDUCTIVITY_MODEL= CONSTANT_CONDUCTIVITY
THERMAL_CONDUCTIVITY_CONSTANT= 0.0179, 0.0258
%
PRANDTL_LAM= 0.72, 0.72
TURBULENT_CONDUCTIVITY_MODEL= CONSTANT_PRANDTL_TURB
PRANDTL_TURB= 0.90, 0.90
%
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
VISCOSITY_MODEL= CONSTANT_VISCOSITY
%
MU_CONSTANT= 8.04E-06, 1.8551E-05
%
MIXING_VISCOSITY_MODEL = WILKE
%
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
MARKER_HEATFLUX= ( wall, 0.0 )
AXISYMMETRIC= YES
MARKER_SYM= ( symmetry )
MARKER_EULER= ( top_wall )
MARKER_INLET_TURBULENT= ( inlet_gas, 0.04, 5, inlet_air, 0.004, 1 )
%
INC_INLET_TYPE= VELOCITY_INLET VELOCITY_INLET
SPECIFIED_INLET_PROFILE= NO
%INLET_FILENAME= inlet_jet.dat
%INLET_MATCHING_TOLERANCE= 1.2E-06
%
MARKER_INLET= ( inlet_gas, 294, 53.0, 1.0, 0.0 0.0, inlet_air, 294, 9.2, 1.0, 0.0, 0.0 )
MARKER_INLET_SPECIES= ( inlet_gas, 1.0, inlet_air, 0.0 )
%
INC_OUTLET_TYPE= PRESSURE_OUTLET
MARKER_OUTLET= ( outlet, 0.0 )
%
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
CFL_NUMBER= 200.0
CFL_ADAPT= NO
CFL_REDUCTION_SPECIES= 1.0
CFL_REDUCTION_TURB= 0.5
%
ITER= 9999
%
% ------------------------ 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= FDS
MUSCL_FLOW= NO
SLOPE_LIMITER_FLOW = NONE
TIME_DISCRE_FLOW= EULER_IMPLICIT
%
% -------------------- SCALAR TRANSPORT ---------------------------------------%
%
KIND_SCALAR_MODEL= SPECIES_TRANSPORT
%
DIFFUSIVITY_MODEL= UNITY_LEWIS
%
SCHMIDT_NUMBER_TURBULENT= 0.7
%
CONV_NUM_METHOD_SPECIES= BOUNDED_SCALAR
MUSCL_SPECIES= NO
SLOPE_LIMITER_SPECIES = NONE
%
TIME_DISCRE_SPECIES= EULER_IMPLICIT
%
SPECIES_INIT= 0.05
SPECIES_CLIPPING= NO
SPECIES_CLIPPING_MIN= 0.0
SPECIES_CLIPPING_MAX= 1.0
%
% -------------------- TURBULENT TRANSPORT ---------------------------------------%
%
CONV_NUM_METHOD_TURB= BOUNDED_SCALAR
MUSCL_TURB= NO
%
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
CONV_FIELD= RMS_PRESSURE, RMS_VELOCITY-X, RMS_VELOCITY-Y, RMS_TKE, RMS_SPECIES
CONV_RESIDUAL_MINVAL= -14.0
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-6
%
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
MESH_FILENAME= MESH_validation.su2
%
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
SCREEN_WRT_FREQ_INNER= 10
%
HISTORY_OUTPUT= ITER RMS_RES LINSOL SPECIES_COEFF SPECIES_COEFF_SURF SURFACE_TOTAL_PRESSURE
CONV_FILENAME= history
MARKER_ANALYZE= inlet_gas,inlet_air, 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.csv
SOLUTION_FILENAME= solution.csv
%
WRT_PERFORMANCE= YES
OUTPUT_PRECISION= 16