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Nested preconditioner test cases
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‎TestCases/TestCases‎

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Subproject commit c0c2d61c43e2c257c01be8c375713bcc0da12a9b

‎TestCases/parallel_regression.py‎

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‎TestCases/rans/naca0012/turb_NACA0012_sa_nested.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: Francisco Palacios %
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% Institution: Stanford University %
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% Date: Feb 18th, 2013 %
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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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SA_OPTIONS= NEGATIVE, EXPERIMENTAL
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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= 0.15
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AOA= 0.0
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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= FGMRESandBCGSTAB2
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LINEAR_SOLVER_PREC= LU_SGS
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LINEAR_SOLVER_ERROR= 1E-5
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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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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= YES
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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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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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% Output the performance summary to the console at the end of SU2_CFD
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WRT_PERFORMANCE= YES
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= n0012_897-257.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_sa
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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=(WALL_TIME, INNER_ITER, RMS_DENSITY, RMS_NU_TILDE, LIFT, DRAG, LINSOL_ITER, LINSOL_RESIDUAL, LINSOL_ITER_TURB, LINSOL_RESIDUAL_TURB, TOTAL_HEATFLUX)

‎TestCases/rans/turb_NACA0012_sa_nested.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: Francisco Palacios %
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% Institution: Stanford University %
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% Date: Feb 18th, 2013 %
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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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SA_OPTIONS= NEGATIVE, EXPERIMENTAL
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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= 0.05
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AOA= 0.0
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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= 200.0
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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= FGMRESandBCGSTAB2
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LINEAR_SOLVER_PREC= LU_SGS
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LINEAR_SOLVER_ERROR= 1E-5
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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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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= YES
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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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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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% Output the performance summary to the console at the end of SU2_CFD
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WRT_PERFORMANCE= YES
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= n0012_897-257.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_sa
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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=(WALL_TIME, INNER_ITER, RMS_DENSITY, RMS_NU_TILDE, LIFT, DRAG, LINSOL_ITER, LINSOL_RESIDUAL, LINSOL_ITER_TURB, LINSOL_RESIDUAL_TURB, TOTAL_HEATFLUX)

‎TestCases/serial_regression.py‎

100644100755
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