su2code · Syphonicc · Aug 11, 2026
diff --git 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
@@ -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
@@ -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
@@ -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
@@ -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
@@ -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
@@ -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
@@ -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
@@ -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
@@ -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