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Add regressions with u-muscl reconstruction
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‎TestCases/parallel_regression.py‎

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@@ -436,6 +436,15 @@ def main():
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turb_oneram6_nk.tol = 0.0001
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test_list.append(turb_oneram6_nk)
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# ONERA M6 Wing - U-MUSCL
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turb_oneram6_umuscl = TestCase('turb_oneram6_umuscl')
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turb_oneram6_umuscl.cfg_dir = "rans/oneram6"
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turb_oneram6_umuscl.cfg_file = "turb_ONERAM6_umuscl.cfg"
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turb_oneram6_umuscl.test_iter = 10
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turb_oneram6_umuscl.test_vals = [-2.226258, -6.527117, 0.227274, 0.117072, 0.000000]
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turb_oneram6_umuscl.timeout = 3200
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test_list.append(turb_oneram6_umuscl)
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# NACA0012 (SA, FUN3D finest grid results: CL=1.0983, CD=0.01242)
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turb_naca0012_sa = TestCase('turb_naca0012_sa')
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turb_naca0012_sa.cfg_dir = "rans/naca0012"
@@ -502,6 +511,16 @@ def main():
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turb_naca0012_sst_expliciteuler.timeout = 3200
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test_list.append(turb_naca0012_sst_expliciteuler)
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# NACA0012 (SST, FUN3D finest grid, U-MUSCL)
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turb_naca0012_sst_umuscl = TestCase('turb_naca0012_sst_umuscl')
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turb_naca0012_sst_umuscl.cfg_dir = "rans/naca0012"
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turb_naca0012_sst_umuscl.cfg_file = "turb_NACA0012_sst_umuscl.cfg"
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turb_naca0012_sst_umuscl.test_iter = 10
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turb_naca0012_sst_umuscl.test_vals = [-12.078069, -15.284102, -5.859484, 1.048053, 0.019238, -2.015780, 0.000000]
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turb_naca0012_sst_umuscl.test_vals_aarch64 = [-12.232530, -14.435294, -6.037147, 1.047444, 0.019214, -1.704457, 0.000000]
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turb_naca0012_sst_umuscl.timeout = 3200
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test_list.append(turb_naca0012_sst_umuscl)
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# PROPELLER
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propeller = TestCase('propeller')
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propeller.cfg_dir = "rans/propeller"

‎TestCases/rans/naca0012/turb_NACA0012_sst_umuscl.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: 2D NACA 0012 Airfoil Validation Case (compressible) %
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% http://turbmodels.larc.nasa.gov/naca0012_val_sa.html %
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% Author: Brian C. Munguía %
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% Institution: Stanford University %
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% Date: 2025.10.16 %
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% File Version 8.3.0 "Harrier" %
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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= RANS
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KIND_TURB_MODEL= SST
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SST_OPTIONS= V1994m
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MATH_PROBLEM= DIRECT
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RESTART_SOL= YES
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READ_BINARY_RESTART= NO
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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MACH_NUMBER= 0.15
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AOA= 10.0
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FREESTREAM_TEMPERATURE= 300.0
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REYNOLDS_NUMBER= 6.0E6
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REYNOLDS_LENGTH= 1.0
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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REF_LENGTH= 1.0
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REF_AREA= 1.0
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REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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MARKER_HEATFLUX= ( airfoil, 0.0 )
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MARKER_FAR= ( farfield )
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MARKER_PLOTTING= ( airfoil )
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MARKER_MONITORING= ( airfoil )
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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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NUM_METHOD_GRAD_RECON= LEAST_SQUARES
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CFL_NUMBER= 1000.0
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MAX_DELTA_TIME= 1E10
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CFL_ADAPT= NO
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CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
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ITER= 99999
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% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
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VENKAT_LIMITER_COEFF= 0.03
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LIMITER_ITER= 99999
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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-10
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LINEAR_SOLVER_ITER= 20
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= ROE
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MUSCL_FLOW= YES
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MUSCL_KAPPA_FLOW= 0.5
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SLOPE_LIMITER_FLOW= NONE
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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MUSCL_TURB= NO
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MUSCL_KAPPA_TURB= 0.0
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SLOPE_LIMITER_TURB= NONE
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TIME_DISCRE_TURB= EULER_IMPLICIT
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CFL_REDUCTION_TURB= 1.0
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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% Convergence field
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CONV_FIELD= RMS_DENSITY
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CONV_RESIDUAL_MINVAL= -12
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CONV_STARTITER= 10
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CONV_CAUCHY_ELEMS= 100
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CONV_CAUCHY_EPS= 1E-6
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= n0012_225-65.su2
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MESH_FORMAT= SU2
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MESH_OUT_FILENAME= mesh_out
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SOLUTION_FILENAME= solution_flow_sst
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SOLUTION_ADJ_FILENAME= solution_adj
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TABULAR_FORMAT= CSV
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CONV_FILENAME= history
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RESTART_FILENAME= restart_flow
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RESTART_ADJ_FILENAME= restart_adj
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VOLUME_FILENAME= flow
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VOLUME_ADJ_FILENAME= adjoint
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GRAD_OBJFUNC_FILENAME= of_grad
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SURFACE_FILENAME= surface_flow
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SURFACE_ADJ_FILENAME= surface_adjoint
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OUTPUT_WRT_FREQ= 10000
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SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_TKE, RMS_DISSIPATION, LIFT, DRAG, LINSOL_RESIDUAL, TOTAL_HEATFLUX)
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OUTPUT_FILES= (RESTART_ASCII, PARAVIEW, SURFACE_PARAVIEW)

‎TestCases/rans/oneram6/turb_ONERAM6_umuscl.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Turbulent flow past the ONERA M6 wing with U-MUSCL recon %
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% Author: Brian C. Munguía %
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% Institution: Stanford University %
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% Date: 2025.10.16 %
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% File Version 8.3.0 "Harrier" %
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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= RANS
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KIND_TURB_MODEL= SA
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MATH_PROBLEM= DIRECT
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RESTART_SOL= NO
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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MACH_NUMBER= 0.8395
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AOA= 3.06
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SIDESLIP_ANGLE= 0.0
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FREESTREAM_TEMPERATURE= 288.15
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REYNOLDS_NUMBER= 11.72E6
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REYNOLDS_LENGTH= 0.64607
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% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
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%
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FLUID_MODEL= STANDARD_AIR
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GAMMA_VALUE= 1.4
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GAS_CONSTANT= 287.058
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CRITICAL_TEMPERATURE= 131.00
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CRITICAL_PRESSURE= 3588550.0
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CRITICAL_DENSITY= 263.0
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ACENTRIC_FACTOR= 0.035
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% --------------------------- VISCOSITY MODEL ---------------------------------%
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%
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VISCOSITY_MODEL= SUTHERLAND
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MU_CONSTANT= 1.716E-5
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MU_REF= 1.716E-5
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MU_T_REF= 273.15
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SUTHERLAND_CONSTANT= 110.4
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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REF_LENGTH= 0.64607
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REF_AREA= 0
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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MARKER_HEATFLUX= ( WING, 0.0 )
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MARKER_FAR= ( FARFIELD )
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MARKER_SYM= ( SYMMETRY )
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MARKER_PLOTTING= ( WING )
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MARKER_MONITORING= ( WING )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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NUM_METHOD_GRAD= GREEN_GAUSS
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CFL_NUMBER= 4.0
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CFL_ADAPT= NO
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CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
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RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
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ITER= 999999
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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= LU_SGS
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LINEAR_SOLVER_ERROR= 1E-4
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LINEAR_SOLVER_ITER= 5
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= ROE
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MUSCL_FLOW= YES
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MUSCL_KAPPA_FLOW= 0.5
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SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
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VENKAT_LIMITER_COEFF= 1.0
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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MUSCL_TURB= NO
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MUSCL_KAPPA_TURB= 0.0
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SLOPE_LIMITER_TURB= NONE
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TIME_DISCRE_TURB= EULER_IMPLICIT
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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CONV_RESIDUAL_MINVAL= -10
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CONV_STARTITER= 10
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CONV_CAUCHY_ELEMS= 100
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CONV_CAUCHY_EPS= 1E-6
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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% These settings are just to reproduce test results, comment them out
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% or delete them to use best practice values.
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PARMETIS_TOLERANCE= 0.05
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PARMETIS_EDGE_WEIGHT= 0
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PARMETIS_POINT_WEIGHT= 1
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MESH_FILENAME= mesh_ONERAM6_turb_hexa_43008.su2
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MESH_FORMAT= SU2
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MESH_OUT_FILENAME= mesh_out
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SOLUTION_FILENAME= restart_flow
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SOLUTION_ADJ_FILENAME= solution_adj
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OUTPUT_FILES=(RESTART, STL_ASCII, PARAVIEW, SURFACE_PARAVIEW)
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TABULAR_FORMAT= CSV
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CONV_FILENAME= history
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RESTART_FILENAME= restart_flow
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RESTART_ADJ_FILENAME= restart_adj
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VOLUME_FILENAME= flow
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VOLUME_ADJ_FILENAME= adjoint
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GRAD_OBJFUNC_FILENAME= of_grad
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SURFACE_FILENAME= surface_flow
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SURFACE_ADJ_FILENAME= surface_adjoint
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OUTPUT_WRT_FREQ= 250
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SCREEN_OUTPUT = (INNER_ITER, RMS_DENSITY, RMS_NU_TILDE, LIFT, DRAG, TOTAL_HEATFLUX)

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