# Incompressible simulation

 Register Blogs Members List Search Today's Posts Mark Forums Read April 15, 2014, 08:54 Incompressible simulation #1 Member   Brugiere Olivier Join Date: Mar 2009 Posts: 34 Rep Power: 15 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: 13 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: 15 Hi, Thanks for your answer. I've find my mistake Regards Olivier  Thread Tools Search this Thread Show Printable Version Email this Page Search this Thread: Advanced Search Display Modes Linear Mode Switch to Hybrid Mode Switch to Threaded Mode Posting Rules You may not post new threads You may not post replies You may not post attachments You may not edit your posts BB code is On Smilies are On [IMG] code is On HTML code is OffTrackbacks are Off Pingbacks are On Refbacks are On Forum Rules Similar Threads Thread Thread Starter Forum Replies Last Post amarjogot Main CFD Forum 0 June 20, 2013 12:26 niels1900 FloEFD, FloWorks & FloTHERM 6 April 20, 2011 10:44 mep10jl FLUENT 0 November 18, 2010 19:25 RPJones FLOW-3D 2 November 9, 2010 08:18 Smagmon CFX 1 March 6, 2009 13:24

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