# Incompressible simulation

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 April 15, 2014, 08:54 Incompressible simulation #1 Member   Brugiere Olivier Join Date: Mar 2009 Posts: 34 Rep Power: 16 hi all, I'm new user of SU2. I would like to make tests of the adjoint solver on a rear-view mirror to reduce the drag coefficient. In SU2 v2.0, I can make a simulation without the adjoint part. I've upgraded my version of SU2 and I can't reproduce this case now. I don't find how to have wall without temperature like with MARKER_NS. To the car and the rear-view mirror, I've four boundary conditions (car, arm, mirror and mirror_plate). If some body can give me some advices, I give my configuration file. Code: ```%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % % % Stanford University unstructured (SU2) configuration file % % Case description: Turbulent flow over flat plate with zero pressure gradient % % Author: Thomas D. Economon % % Institution: Stanford University % % Date: 2011.11.10 % % File Version 1.0.12 January 5th, 2012 % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% % % Physical governing equations (EULER, NAVIER_STOKES, % TNE2_EULER, TNE2_NAVIER_STOKES, % WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY, % POISSON_EQUATION) PHYSICAL_PROBLEM= NAVIER_STOKES % % Specify turbulence model (NONE, SA, SST) KIND_TURB_MODEL= SA % % Mathematical problem (DIRECT, ADJOINT, LINEARIZED) MATH_PROBLEM= DIRECT % % Restart solution (NO, YES) RESTART_SOL= NO % % Regime type (COMPRESSIBLE, INCOMPRESSIBLE, FREESURFACE) REGIME_TYPE= INCOMPRESSIBLE % % Gravity force, only incompressible (NO, YES) GRAVITY_FORCE= NO % % Axisymmetric simulation, only compressible (NO, YES) AXISYMMETRIC= NO % % Perform a low fidelity simulation (NO, YES) LOW_FIDELITY_SIMULATION= NO % -------------------- INCOMPRESSIBLE FREE-STREAM DEFINITION ------------------% % % Free-stream density (1.2886 Kg/m^3 (air), 998.2 Kg/m^3 (water)) FREESTREAM_DENSITY= 1.2886 % % Free-stream velocity (m/s) FREESTREAM_VELOCITY= ( 33.3333, 0.00, 0.00 ) % 120 km/h % % Free-stream viscosity (1.853E-5 Ns/m^2 (air), 0.798E-3 Ns/m^2 (water)) FREESTREAM_VISCOSITY= 1.853E-5 % -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------% % % Ratio of specific heats (1.4 (air), only for compressible flows) GAMMA_VALUE= 1.4 % % Specific gas constant (287.87 J/kg*K (air), only for compressible flows) GAS_CONSTANT= 287.87 % % Laminar Prandtl number (0.72 (air), only for compressible flows) PRANDTL_LAM= 0.72 % % Turbulent Prandtl number (0.9 (air), only for compressible flows) PRANDTL_TURB= 0.9 % % Value of the Bulk Modulus (1.42E5 N/m^2 (air), 2.2E9 N/m^2 (water), % only for incompressible flows) BULK_MODULUS= 1.42E5 % % Artifical compressibility factor (1.0 by default, % only for incompressible flows) ARTCOMP_FACTOR= 1.0 % ---------------------- REFERENCE VALUE DEFINITION ---------------------------% % % Reference origin for moment computation REF_ORIGIN_MOMENT_X = 0.547 REF_ORIGIN_MOMENT_Y = -0.786 REF_ORIGIN_MOMENT_Z = 0.811 % % Reference length for pitching, rolling, and yawing non-dimensional moment REF_LENGTH_MOMENT= 0.205 % % Reference area for force coefficients (0 implies automatic calculation) REF_AREA= 0 % ------------------------- UNSTEADY SIMULATION -------------------------------% % % Unsteady simulation (NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, % DUAL_TIME_STEPPING-2ND_ORDER) UNSTEADY_SIMULATION= NO % % Time Step for dual time stepping simulations (s) UNST_TIMESTEP= 0.0 % % Total Physical Time for dual time stepping simulations (s) UNST_TIME= 50.0 % % Unsteady Courant-Friedrichs-Lewy number of the finest grid UNST_CFL_NUMBER= 0.0 % % Number of internal iterations (dual time method) UNST_INT_ITER= 200 % % Integer number of periodic time instances for Time Spectral TIME_INSTANCES= 1 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------% % % Navier-Stokes wall boundary marker(s) (NONE = no marker) MARKER_ISOTHERMAL= ( car, mirror, mirror_plate, bras ) % % Farfield boundary marker(s) (NONE = no marker) MARKER_FAR= ( inlet, bottom, top_4, side+, outlet_2 ) % % Symmetry boundary marker(s) (NONE = no marker) MARKER_SYM= ( side- ) % ------------------------ SURFACES IDENTIFICATION ----------------------------% % % Marker(s) of the surface to be plotted or designed MARKER_PLOTTING= ( mirror, mirror_plate, bras ) % % Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated MARKER_MONITORING= ( mirror, mirror_plate, bras ) % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% % % Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES % % Courant-Friedrichs-Lewy condition of the finest grid CFL_NUMBER= 5.0 % % CFL ramp (factor, number of iterations, CFL limit) CFL_RAMP= ( 1.1, 100, 20.0 ) % % Runge-Kutta alpha coefficients RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) % % Number of total iterations EXT_ITER= 30 % -------------------------- MULTIGRID PARAMETERS -----------------------------% % % Multi-Grid Levels (0 = no multi-grid) MGLEVEL= 2 % % Multi-Grid Cycle (0 = V cycle, 1 = W Cycle) MGCYCLE= 0 % % CFL reduction factor on the coarse levels MG_CFL_REDUCTION= 0.75 % % Maximum number of children in the agglomeration stage MAX_CHILDREN= 250 % % Maximum length of an agglomerated element (relative to the domain) MAX_DIMENSION= 0.1 % % Multigrid pre-smoothing level MG_PRE_SMOOTH= ( 1, 2, 3, 3 ) % % Multigrid post-smoothing level MG_POST_SMOOTH= ( 0, 0, 0, 0 ) % % Jacobi implicit smoothing of the correction MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 ) % % Damping factor for the residual restriction MG_DAMP_RESTRICTION= 0.5 % % Damping factor for the correction prolongation MG_DAMP_PROLONGATION= 0.5 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% % % Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, % TURKEL_PREC, MSW) CONV_NUM_METHOD_FLOW= ROE % % Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER) % SPATIAL_ORDER_FLOW= 2ND_ORDER % % Slope limiter (VENKATAKRISHNAN, MINMOD) SLOPE_LIMITER_FLOW= VENKATAKRISHNAN % % Coefficient for the limiter LIMITER_COEFF= 0.3 % % 1st, 2nd and 4th order artificial dissipation coefficients AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 ) % % Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED, GALERKIN) VISC_NUM_METHOD_FLOW= AVG_GRAD_CORRECTED % % Source term numerical method (PIECEWISE_CONSTANT) SOUR_NUM_METHOD_FLOW= PIECEWISE_CONSTANT % % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) TIME_DISCRE_FLOW= EULER_IMPLICIT % -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------% % % Convective numerical method (SCALAR_UPWIND) CONV_NUM_METHOD_TURB= SCALAR_UPWIND % % Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER) SPATIAL_ORDER_TURB= 2ND_ORDER % % Slope limiter (VENKATAKRISHNAN, MINMOD) SLOPE_LIMITER_TURB= VENKATAKRISHNAN % % Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED) VISC_NUM_METHOD_TURB= AVG_GRAD_CORRECTED % % Source term numerical method (PIECEWISE_CONSTANT) SOUR_NUM_METHOD_TURB= PIECEWISE_CONSTANT % % Time discretization (EULER_IMPLICIT) TIME_DISCRE_TURB= EULER_IMPLICIT % % Reduction factor of the CFL coefficient in the turbulence problem CFL_REDUCTION_TURB= 1.0 % --------------------------- PARTITIONING STRATEGY ---------------------------% % % Write a paraview file for each partition (NO, YES) VISUALIZE_PART= NO % --------------------------- CONVERGENCE PARAMETERS --------------------------% % % Convergence criteria (CAUCHY, RESIDUAL) % CONV_CRITERIA= RESIDUAL % % Residual reduction (order of magnitude with respect to the initial value) RESIDUAL_REDUCTION= 8 % % Min value of the residual (log10 of the residual) RESIDUAL_MINVAL= -10 % % Start convergence criteria at iteration number STARTCONV_ITER= 10 % % Number of elements to apply the criteria CAUCHY_ELEMS= 100 % % Epsilon to control the series convergence CAUCHY_EPS= 1E-6 % % Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY, % SENS_MACH, DELTA_LIFT, DELTA_DRAG) CAUCHY_FUNC_FLOW= DRAG % % Epsilon for full multigrid method evaluation FULLMG_CAUCHY_EPS= 1E-4 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % % Mesh input file MESH_FILENAME= Retro.su2 % % Mesh input file format (SU2, CGNS, NETCDF_ASCII) MESH_FORMAT= SU2 % % Convert a CGNS mesh to SU2 format (YES, NO) CGNS_TO_SU2= NO % % Mesh output file MESH_OUT_FILENAME= mesh_out.su2 % % Restart flow input file SOLUTION_FLOW_FILENAME= solution_flow.dat % % Restart adjoint input file SOLUTION_ADJ_FILENAME= solution_adj.dat % % Output file format (PARAVIEW, TECPLOT, SLT) OUTPUT_FORMAT= PARAVIEW % % Output file convergence history (w/o extension) CONV_FILENAME= history % % Output file restart flow RESTART_FLOW_FILENAME= restart_flow.dat % % Output file restart adjoint RESTART_ADJ_FILENAME= restart_adj.dat % % Output file linear flow RESTART_LIN_FILENAME= restart_lin.dat % % Output file flow (w/o extension) variables VOLUME_FLOW_FILENAME= flow % % Output file adjoint (w/o extension) variables VOLUME_ADJ_FILENAME= adjoint % % Output file linearized (w/o extension) variables VOLUME_LIN_FILENAME= linearized % % Output objective function gradient (using continuous adjoint) GRAD_OBJFUNC_FILENAME= of_grad.dat % % Output file surface flow coefficient (w/o extension) SURFACE_FLOW_FILENAME= surface_flow % % Output file surface adjoint coefficient (w/o extension) SURFACE_ADJ_FILENAME= surface_adjoint % % Output file surface linear coefficient (w/o extension) SURFACE_LIN_FILENAME= surface_linear % % Writing solution file frequency WRT_SOL_FREQ= 10 % % Writing convergence history frequency WRT_CON_FREQ= 1 % % Write unsteady data adding headers and prefixes (NO, YES) WRT_UNSTEADY= NO``` Thanks for your answers Regards Olivier

April 15, 2014, 09:59
#2
Senior Member

Join Date: Nov 2010
Posts: 139
Rep Power: 14
Hi,
Simply replace the Navier-Stokes makers in your config file with the following parameter:

%
% Navier-Stokes wall boundary marker(s) (NONE = no marker)
MARKER_HEATFLUX= ( car, 0.0 )
and so on for the rest of boundary markers.

NOTE: Normally you should find all the updates within the config_template.cfg file supplied with each release of SU2.

Hope this helps
Taxalian.

Quote:
 Originally Posted by brugiere_olivier hi all, I'm new user of SU2. I would like to make tests of the adjoint solver on a rear-view mirror to reduce the drag coefficient. In SU2 v2.0, I can make a simulation without the adjoint part. I've upgraded my version of SU2 and I can't reproduce this case now. I don't find how to have wall without temperature like with MARKER_NS. To the car and the rear-view mirror, I've four boundary conditions (car, arm, mirror and mirror_plate). If some body can give me some advices, I give my configuration file. Code: ```%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % % % Stanford University unstructured (SU2) configuration file % % Case description: Turbulent flow over flat plate with zero pressure gradient % % Author: Thomas D. Economon % % Institution: Stanford University % % Date: 2011.11.10 % % File Version 1.0.12 January 5th, 2012 % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% % % Physical governing equations (EULER, NAVIER_STOKES, % TNE2_EULER, TNE2_NAVIER_STOKES, % WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY, % POISSON_EQUATION) PHYSICAL_PROBLEM= NAVIER_STOKES % % Specify turbulence model (NONE, SA, SST) KIND_TURB_MODEL= SA % % Mathematical problem (DIRECT, ADJOINT, LINEARIZED) MATH_PROBLEM= DIRECT % % Restart solution (NO, YES) RESTART_SOL= NO % % Regime type (COMPRESSIBLE, INCOMPRESSIBLE, FREESURFACE) REGIME_TYPE= INCOMPRESSIBLE % % Gravity force, only incompressible (NO, YES) GRAVITY_FORCE= NO % % Axisymmetric simulation, only compressible (NO, YES) AXISYMMETRIC= NO % % Perform a low fidelity simulation (NO, YES) LOW_FIDELITY_SIMULATION= NO % -------------------- INCOMPRESSIBLE FREE-STREAM DEFINITION ------------------% % % Free-stream density (1.2886 Kg/m^3 (air), 998.2 Kg/m^3 (water)) FREESTREAM_DENSITY= 1.2886 % % Free-stream velocity (m/s) FREESTREAM_VELOCITY= ( 33.3333, 0.00, 0.00 ) % 120 km/h % % Free-stream viscosity (1.853E-5 Ns/m^2 (air), 0.798E-3 Ns/m^2 (water)) FREESTREAM_VISCOSITY= 1.853E-5 % -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------% % % Ratio of specific heats (1.4 (air), only for compressible flows) GAMMA_VALUE= 1.4 % % Specific gas constant (287.87 J/kg*K (air), only for compressible flows) GAS_CONSTANT= 287.87 % % Laminar Prandtl number (0.72 (air), only for compressible flows) PRANDTL_LAM= 0.72 % % Turbulent Prandtl number (0.9 (air), only for compressible flows) PRANDTL_TURB= 0.9 % % Value of the Bulk Modulus (1.42E5 N/m^2 (air), 2.2E9 N/m^2 (water), % only for incompressible flows) BULK_MODULUS= 1.42E5 % % Artifical compressibility factor (1.0 by default, % only for incompressible flows) ARTCOMP_FACTOR= 1.0 % ---------------------- REFERENCE VALUE DEFINITION ---------------------------% % % Reference origin for moment computation REF_ORIGIN_MOMENT_X = 0.547 REF_ORIGIN_MOMENT_Y = -0.786 REF_ORIGIN_MOMENT_Z = 0.811 % % Reference length for pitching, rolling, and yawing non-dimensional moment REF_LENGTH_MOMENT= 0.205 % % Reference area for force coefficients (0 implies automatic calculation) REF_AREA= 0 % ------------------------- UNSTEADY SIMULATION -------------------------------% % % Unsteady simulation (NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, % DUAL_TIME_STEPPING-2ND_ORDER) UNSTEADY_SIMULATION= NO % % Time Step for dual time stepping simulations (s) UNST_TIMESTEP= 0.0 % % Total Physical Time for dual time stepping simulations (s) UNST_TIME= 50.0 % % Unsteady Courant-Friedrichs-Lewy number of the finest grid UNST_CFL_NUMBER= 0.0 % % Number of internal iterations (dual time method) UNST_INT_ITER= 200 % % Integer number of periodic time instances for Time Spectral TIME_INSTANCES= 1 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------% % % Navier-Stokes wall boundary marker(s) (NONE = no marker) MARKER_ISOTHERMAL= ( car, mirror, mirror_plate, bras ) % % Farfield boundary marker(s) (NONE = no marker) MARKER_FAR= ( inlet, bottom, top_4, side+, outlet_2 ) % % Symmetry boundary marker(s) (NONE = no marker) MARKER_SYM= ( side- ) % ------------------------ SURFACES IDENTIFICATION ----------------------------% % % Marker(s) of the surface to be plotted or designed MARKER_PLOTTING= ( mirror, mirror_plate, bras ) % % Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated MARKER_MONITORING= ( mirror, mirror_plate, bras ) % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% % % Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES % % Courant-Friedrichs-Lewy condition of the finest grid CFL_NUMBER= 5.0 % % CFL ramp (factor, number of iterations, CFL limit) CFL_RAMP= ( 1.1, 100, 20.0 ) % % Runge-Kutta alpha coefficients RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) % % Number of total iterations EXT_ITER= 30 % -------------------------- MULTIGRID PARAMETERS -----------------------------% % % Multi-Grid Levels (0 = no multi-grid) MGLEVEL= 2 % % Multi-Grid Cycle (0 = V cycle, 1 = W Cycle) MGCYCLE= 0 % % CFL reduction factor on the coarse levels MG_CFL_REDUCTION= 0.75 % % Maximum number of children in the agglomeration stage MAX_CHILDREN= 250 % % Maximum length of an agglomerated element (relative to the domain) MAX_DIMENSION= 0.1 % % Multigrid pre-smoothing level MG_PRE_SMOOTH= ( 1, 2, 3, 3 ) % % Multigrid post-smoothing level MG_POST_SMOOTH= ( 0, 0, 0, 0 ) % % Jacobi implicit smoothing of the correction MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 ) % % Damping factor for the residual restriction MG_DAMP_RESTRICTION= 0.5 % % Damping factor for the correction prolongation MG_DAMP_PROLONGATION= 0.5 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% % % Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, % TURKEL_PREC, MSW) CONV_NUM_METHOD_FLOW= ROE % % Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER) % SPATIAL_ORDER_FLOW= 2ND_ORDER % % Slope limiter (VENKATAKRISHNAN, MINMOD) SLOPE_LIMITER_FLOW= VENKATAKRISHNAN % % Coefficient for the limiter LIMITER_COEFF= 0.3 % % 1st, 2nd and 4th order artificial dissipation coefficients AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 ) % % Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED, GALERKIN) VISC_NUM_METHOD_FLOW= AVG_GRAD_CORRECTED % % Source term numerical method (PIECEWISE_CONSTANT) SOUR_NUM_METHOD_FLOW= PIECEWISE_CONSTANT % % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) TIME_DISCRE_FLOW= EULER_IMPLICIT % -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------% % % Convective numerical method (SCALAR_UPWIND) CONV_NUM_METHOD_TURB= SCALAR_UPWIND % % Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER) SPATIAL_ORDER_TURB= 2ND_ORDER % % Slope limiter (VENKATAKRISHNAN, MINMOD) SLOPE_LIMITER_TURB= VENKATAKRISHNAN % % Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED) VISC_NUM_METHOD_TURB= AVG_GRAD_CORRECTED % % Source term numerical method (PIECEWISE_CONSTANT) SOUR_NUM_METHOD_TURB= PIECEWISE_CONSTANT % % Time discretization (EULER_IMPLICIT) TIME_DISCRE_TURB= EULER_IMPLICIT % % Reduction factor of the CFL coefficient in the turbulence problem CFL_REDUCTION_TURB= 1.0 % --------------------------- PARTITIONING STRATEGY ---------------------------% % % Write a paraview file for each partition (NO, YES) VISUALIZE_PART= NO % --------------------------- CONVERGENCE PARAMETERS --------------------------% % % Convergence criteria (CAUCHY, RESIDUAL) % CONV_CRITERIA= RESIDUAL % % Residual reduction (order of magnitude with respect to the initial value) RESIDUAL_REDUCTION= 8 % % Min value of the residual (log10 of the residual) RESIDUAL_MINVAL= -10 % % Start convergence criteria at iteration number STARTCONV_ITER= 10 % % Number of elements to apply the criteria CAUCHY_ELEMS= 100 % % Epsilon to control the series convergence CAUCHY_EPS= 1E-6 % % Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY, % SENS_MACH, DELTA_LIFT, DELTA_DRAG) CAUCHY_FUNC_FLOW= DRAG % % Epsilon for full multigrid method evaluation FULLMG_CAUCHY_EPS= 1E-4 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % % Mesh input file MESH_FILENAME= Retro.su2 % % Mesh input file format (SU2, CGNS, NETCDF_ASCII) MESH_FORMAT= SU2 % % Convert a CGNS mesh to SU2 format (YES, NO) CGNS_TO_SU2= NO % % Mesh output file MESH_OUT_FILENAME= mesh_out.su2 % % Restart flow input file SOLUTION_FLOW_FILENAME= solution_flow.dat % % Restart adjoint input file SOLUTION_ADJ_FILENAME= solution_adj.dat % % Output file format (PARAVIEW, TECPLOT, SLT) OUTPUT_FORMAT= PARAVIEW % % Output file convergence history (w/o extension) CONV_FILENAME= history % % Output file restart flow RESTART_FLOW_FILENAME= restart_flow.dat % % Output file restart adjoint RESTART_ADJ_FILENAME= restart_adj.dat % % Output file linear flow RESTART_LIN_FILENAME= restart_lin.dat % % Output file flow (w/o extension) variables VOLUME_FLOW_FILENAME= flow % % Output file adjoint (w/o extension) variables VOLUME_ADJ_FILENAME= adjoint % % Output file linearized (w/o extension) variables VOLUME_LIN_FILENAME= linearized % % Output objective function gradient (using continuous adjoint) GRAD_OBJFUNC_FILENAME= of_grad.dat % % Output file surface flow coefficient (w/o extension) SURFACE_FLOW_FILENAME= surface_flow % % Output file surface adjoint coefficient (w/o extension) SURFACE_ADJ_FILENAME= surface_adjoint % % Output file surface linear coefficient (w/o extension) SURFACE_LIN_FILENAME= surface_linear % % Writing solution file frequency WRT_SOL_FREQ= 10 % % Writing convergence history frequency WRT_CON_FREQ= 1 % % Write unsteady data adding headers and prefixes (NO, YES) WRT_UNSTEADY= NO``` Thanks for your answers Regards Olivier

 April 15, 2014, 10:12 #3 Member   Brugiere Olivier Join Date: Mar 2009 Posts: 34 Rep Power: 16 Hi, Thanks for your answer. I've find my mistake Regards Olivier