diff --git a/TestCases/control_surface/inv_ONERAM6_moving.cfg b/TestCases/control_surface/inv_ONERAM6_moving.cfg index a06f1eef19f..3ff772b9f85 100644 --- a/TestCases/control_surface/inv_ONERAM6_moving.cfg +++ b/TestCases/control_surface/inv_ONERAM6_moving.cfg @@ -52,7 +52,7 @@ CFL_NUMBER= 5.0 CFL_ADAPT= NO CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -EXT_ITER= 99999 +ITER= 99999 LINEAR_SOLVER= FGMRES LINEAR_SOLVER_ERROR= 1E-6 LINEAR_SOLVER_ITER= 5 diff --git a/TestCases/control_surface/inv_ONERAM6_setting.cfg b/TestCases/control_surface/inv_ONERAM6_setting.cfg index 6a00be3a9ea..296662b6b42 100644 --- a/TestCases/control_surface/inv_ONERAM6_setting.cfg +++ b/TestCases/control_surface/inv_ONERAM6_setting.cfg @@ -52,7 +52,7 @@ CFL_NUMBER= 5.0 CFL_ADAPT= NO CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -EXT_ITER= 99999 +ITER= 99999 LINEAR_SOLVER= FGMRES LINEAR_SOLVER_ERROR= 1E-6 LINEAR_SOLVER_ITER= 5 diff --git a/TestCases/euler/CRM/inv_CRM_JST.cfg b/TestCases/euler/CRM/inv_CRM_JST.cfg index 63c749021f2..86041b533b7 100644 --- a/TestCases/euler/CRM/inv_CRM_JST.cfg +++ b/TestCases/euler/CRM/inv_CRM_JST.cfg @@ -47,7 +47,7 @@ CFL_NUMBER= 5.0 CFL_ADAPT= NO CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -EXT_ITER= 99999 +ITER= 99999 LINEAR_SOLVER= FGMRES LINEAR_SOLVER_ERROR= 1E-1 LINEAR_SOLVER_ITER= 3 diff --git a/TestCases/euler/biparabolic/EA_TEST.cfg b/TestCases/euler/biparabolic/EA_TEST.cfg new file mode 100644 index 00000000000..e216f440870 --- /dev/null +++ b/TestCases/euler/biparabolic/EA_TEST.cfg @@ -0,0 +1,115 @@ +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% +% % +% SU2 configuration file % +% Case description: Supersonic inviscid flow around a biparabolic airfoil % +% Author: Trent W. Lukaczyk % +% Institution: Stanford University % +% Date: 2012.08.16 % +% File Version 8.5.0 "Harrier" % +% % +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% + +% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% +% +SOLVER= EULER +MATH_PROBLEM= DIRECT +RESTART_SOL= NO + +% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------% +% +MACH_NUMBER= 1.7 +AOA= 0.0 +FREESTREAM_PRESSURE= 101325.0 +FREESTREAM_TEMPERATURE= 288.15 + +% ---------------------- 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= 1.0 + +% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% +% +MARKER_EULER= ( airfoil ) +MARKER_FAR= ( farfield ) +MARKER_PLOTTING= ( airfoil ) +MARKER_MONITORING= ( airfoil ) + +% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% +% +NUM_METHOD_GRAD= GREEN_GAUSS +CFL_NUMBER= 2.0 +CFL_ADAPT= YES +CFL_ADAPT_PARAM= ( 0.5, 1.5, 1.0, 50.0 ) +ITER= 500 + +% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------% +% + +OBJECTIVE_FUNCTION= EQUIVALENT_AREA +CONV_NUM_METHOD_ADJFLOW= JST +ADJ_SHARP_LIMITER_COEFF= 3.0 +ADJ_JST_SENSOR_COEFF= ( 0.0, 0.02 ) +CFL_REDUCTION_ADJFLOW= 0.8 +TIME_DISCRE_ADJFLOW= EULER_IMPLICIT + +% ------------------------ GRID DEFORMATION PARAMETERS ------------------------% +% + +DV_KIND= PARABOLIC +DV_MARKER= ( airfoil ) +DV_PARAM= ( 0.5, 5 ) +DV_VALUE= 0.01 +HOLD_GRID_FIXED= YES +HOLD_GRID_FIXED_COORD= ( -0.2, -0.4, 0.0, 2.2, 0.4, 0.0 ) + +% -------------------------- MULTIGRID PARAMETERS -----------------------------% +% + +MGLEVEL= 0 + +% ------------------------ SUPERSONIC SIMULATION ------------------------------% +% + +% Equivalent-area / nearfield setup for sonic-boom studies. Disabled for the +% direct solve: enabling these produces 760 non-physical points and rms[Rho] +% stalls at +3.4 instead of -3.9. Re-enable together with MARKER_NEARFIELD +% below (and remove those two markers from MARKER_FAR) for adjoint EA work. +% + EQUIV_AREA= YES + EA_INT_LIMIT= ( 1.562, 4.562, 2.0 ) + MARKER_NEARFIELD= ( upper_nearfield, lower_nearfield ) + EA_SCALE_FACTOR= 1.0 + +% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% +% +CONV_NUM_METHOD_FLOW= ROE +MUSCL_FLOW= YES +SLOPE_LIMITER_FLOW= VENKATAKRISHNAN +VENKAT_LIMITER_COEFF= 0.05 +TIME_DISCRE_FLOW= EULER_IMPLICIT + +% --------------------------- CONVERGENCE PARAMETERS --------------------------% +% +CONV_RESIDUAL_MINVAL= -6 +CONV_STARTITER= 10 + +% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% +% +MESH_FILENAME= mesh_BIPARABOLIC_sup.su2 +MESH_FORMAT= SU2 +MESH_OUT_FILENAME= mesh_out +SOLUTION_FILENAME= solution_flow +SOLUTION_ADJ_FILENAME= solution_adj +TABULAR_FORMAT= CSV +CONV_FILENAME= history +RESTART_FILENAME= restart_flow +RESTART_ADJ_FILENAME= restart_adj +VOLUME_FILENAME= volume_flow +VOLUME_ADJ_FILENAME= volume_adjoint +GRAD_OBJFUNC_FILENAME= of_grad +SURFACE_FILENAME= surface_flow +SURFACE_ADJ_FILENAME= surface_adjoint +OUTPUT_WRT_FREQ= 500 diff --git a/TestCases/euler/biparabolic/NF_ONLY.cfg b/TestCases/euler/biparabolic/NF_ONLY.cfg new file mode 100644 index 00000000000..39a6156911e --- /dev/null +++ b/TestCases/euler/biparabolic/NF_ONLY.cfg @@ -0,0 +1,116 @@ +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% +% % +% SU2 configuration file % +% Case description: Supersonic inviscid flow around a biparabolic airfoil % +% Author: Trent W. Lukaczyk % +% Institution: Stanford University % +% Date: 2012.08.16 % +% File Version 8.5.0 "Harrier" % +% % +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% + +% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% +% +SOLVER= EULER +MATH_PROBLEM= DIRECT +RESTART_SOL= NO + +% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------% +% +MACH_NUMBER= 1.7 +AOA= 0.0 +FREESTREAM_PRESSURE= 101325.0 +FREESTREAM_TEMPERATURE= 288.15 + +% ---------------------- 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= 1.0 + +% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% +% +MARKER_EULER= ( airfoil ) +MARKER_FAR= ( farfield) +MARKER_PLOTTING= ( airfoil ) +MARKER_MONITORING= ( airfoil ) + + +% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% +% +NUM_METHOD_GRAD= GREEN_GAUSS +CFL_NUMBER= 2.0 +CFL_ADAPT= YES +CFL_ADAPT_PARAM= ( 0.5, 1.5, 1.0, 50.0 ) +ITER= 500 + +% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------% +% + +OBJECTIVE_FUNCTION= EQUIVALENT_AREA +CONV_NUM_METHOD_ADJFLOW= JST +ADJ_SHARP_LIMITER_COEFF= 3.0 +ADJ_JST_SENSOR_COEFF= ( 0.0, 0.02 ) +CFL_REDUCTION_ADJFLOW= 0.8 +TIME_DISCRE_ADJFLOW= EULER_IMPLICIT + +% ------------------------ GRID DEFORMATION PARAMETERS ------------------------% +% + +DV_KIND= PARABOLIC +DV_MARKER= ( airfoil ) +DV_PARAM= ( 0.5, 5 ) +DV_VALUE= 0.01 +HOLD_GRID_FIXED= YES +HOLD_GRID_FIXED_COORD= ( -0.2, -0.4, 0.0, 2.2, 0.4, 0.0 ) + +% -------------------------- MULTIGRID PARAMETERS -----------------------------% +% + +MGLEVEL= 0 + +% ------------------------ SUPERSONIC SIMULATION ------------------------------% +% + +% Equivalent-area / nearfield setup for sonic-boom studies. Disabled for the +% direct solve: enabling these produces 760 non-physical points and rms[Rho] +% stalls at +3.4 instead of -3.9. Re-enable together with MARKER_NEARFIELD +% below (and remove those two markers from MARKER_FAR) for adjoint EA work. +% +% EQUIV_AREA= YES +% EA_INT_LIMIT= ( -100.0, 100.0, 2.0 ) + MARKER_NEARFIELD= ( upper_nearfield, lower_nearfield ) + + +% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% +% +CONV_NUM_METHOD_FLOW= ROE +MUSCL_FLOW= YES +SLOPE_LIMITER_FLOW= VENKATAKRISHNAN +VENKAT_LIMITER_COEFF= 0.05 +TIME_DISCRE_FLOW= EULER_IMPLICIT + +% --------------------------- CONVERGENCE PARAMETERS --------------------------% +% +CONV_RESIDUAL_MINVAL= -6 +CONV_STARTITER= 10 + +% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% +% +MESH_FILENAME= mesh_BIPARABOLIC_sup.su2 +MESH_FORMAT= SU2 +MESH_OUT_FILENAME= mesh_out +SOLUTION_FILENAME= solution_flow +SOLUTION_ADJ_FILENAME= solution_adj +TABULAR_FORMAT= CSV +CONV_FILENAME= history +RESTART_FILENAME= restart_flow +RESTART_ADJ_FILENAME= restart_adj +VOLUME_FILENAME= volume_flow +VOLUME_ADJ_FILENAME= volume_adjoint +GRAD_OBJFUNC_FILENAME= of_grad +SURFACE_FILENAME= surface_flow +SURFACE_ADJ_FILENAME= surface_adjoint +OUTPUT_WRT_FREQ= 500 diff --git a/TestCases/euler/channel/inv_channel.cfg b/TestCases/euler/channel/inv_channel.cfg index 5161a04413d..9736f843fba 100644 --- a/TestCases/euler/channel/inv_channel.cfg +++ b/TestCases/euler/channel/inv_channel.cfg @@ -51,7 +51,7 @@ CFL_NUMBER= 6.0 CFL_ADAPT= NO CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -EXT_ITER= 999999 +ITER= 999999 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------% % diff --git a/TestCases/navierstokes/naca0012/lam_NACA0012.cfg b/TestCases/navierstokes/naca0012/lam_NACA0012.cfg index c6e40834d62..faca2e846de 100644 --- a/TestCases/navierstokes/naca0012/lam_NACA0012.cfg +++ b/TestCases/navierstokes/naca0012/lam_NACA0012.cfg @@ -46,7 +46,7 @@ CFL_NUMBER= 1.0 CFL_ADAPT= NO CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -EXT_ITER= 99999 +ITER= 99999 LINEAR_SOLVER= FGMRES LINEAR_SOLVER_ERROR= 1E-1 LINEAR_SOLVER_ITER= 3 diff --git a/TestCases/rans/flatplate/turb_SST_flatplate.cfg b/TestCases/rans/flatplate/turb_SST_flatplate.cfg index b4e8e5ab7ef..9b4109ee0b3 100644 --- a/TestCases/rans/flatplate/turb_SST_flatplate.cfg +++ b/TestCases/rans/flatplate/turb_SST_flatplate.cfg @@ -49,7 +49,7 @@ CFL_NUMBER= 10.0 CFL_ADAPT= NO CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -EXT_ITER= 99999 +ITER= 99999 % ----------------------- SLOPE LIMITER DEFINITION ----------------------------% % diff --git a/TestCases/rans/s809/turb_S809.cfg b/TestCases/rans/s809/turb_S809.cfg index 4b36e58d583..4b8f8621035 100644 --- a/TestCases/rans/s809/turb_S809.cfg +++ b/TestCases/rans/s809/turb_S809.cfg @@ -46,7 +46,7 @@ NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES CFL_NUMBER= 10.0 CFL_ADAPT= NO CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) -EXT_ITER= 99999 +ITER= 99999 LINEAR_SOLVER= FGMRES LINEAR_SOLVER_ERROR= 1E-4 LINEAR_SOLVER_ITER= 2 diff --git a/TestCases/rans_uq/naca0012/turb_NACA0012_uq.cfg b/TestCases/rans_uq/naca0012/turb_NACA0012_uq.cfg index ec4658f7bb4..b19c73f901b 100644 --- a/TestCases/rans_uq/naca0012/turb_NACA0012_uq.cfg +++ b/TestCases/rans_uq/naca0012/turb_NACA0012_uq.cfg @@ -48,7 +48,7 @@ CFL_NUMBER= 10.0 MAX_DELTA_TIME= 1E10 CFL_ADAPT= YES CFL_ADAPT_PARAM= ( 0.1, 1.2, 10.0, 100.0 ) -EXT_ITER= 10 +ITER= 10 % ----------------------- SLOPE LIMITER DEFINITION ----------------------------% VENKAT_LIMITER_COEFF= 0.03