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November 26, 2021, 06:42 |
CFG file for Nozzle
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New Member
Nicola Fontana
Join Date: Nov 2021
Posts: 8
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Hi everyone,
I would like to ask if anyone could help me or provide me general infromation about the settings of the configuration file for this two mesh. I already tried with different settings, but I can't get convergence in both case. I can't figure out if the problem is in the boundary condition or in the setting of convergence criteria. 1. Subsonic Converging Nozzle In this case I would like to simulate the subsonic flow throught the nozzle, including the outern region; Code:
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % % % SU2 configuration file % % Case description: Air flow in converging nozzle % % % % Author: Nicola Fontana % % Institution: % % Date: 24.11.2021 % % File Version 7.2 % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% % % Physical governing equations (EULER, NAVIER_STOKES, % FEM_EULER, FEM_NAVIER_STOKES, FEM_RANS, FEM_LES, % WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY, % POISSON_EQUATION) % %SOLVER = EULER % SOLVER= RANS % % Specify turbulence model (NONE, SA, SA_NEG, SST, SA_E, SA_COMP, SA_E_COMP) KIND_TURB_MODEL= SA % % Mathematical problem (DIRECT, CONTINUOUS_ADJOINT, DISCRETE_ADJOINT) MATH_PROBLEM= DIRECT % % Restart solution (NO, YES) RESTART_SOL= NO % % System of measurements (SI, US) % International system of units (SI): ( meters, kilograms, Kelvins, % Newtons = kg m/s^2, Pascals = N/m^2, % Density = kg/m^3, Speed = m/s, % Equiv. Area = m^2 ) % United States customary units (US): ( inches, slug, Rankines, lbf = slug ft/s^2, % psf = lbf/ft^2, Density = slug/ft^3, % Speed = ft/s, Equiv. Area = ft^2 ) SYSTEM_MEASUREMENTS= SI % % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% % % Mach number (non-dimensional, based on the free-stream values) MACH_NUMBER= 1E-9 % % Angle of attack (degrees, only for compressible flows) AOA= 0.0 % % Side-slip angle (degrees, only for compressible flows) SIDESLIP_ANGLE= 0.0 % % Init option to choose between Reynolds (default) or thermodynamics quantities % for initializing the solution (REYNOLDS, TD_CONDITIONS) INIT_OPTION= TD_CONDITIONS % % Free-stream option to choose between density and temperature (default) for % initializing the solution (TEMPERATURE_FS, DENSITY_FS) FREESTREAM_OPTION= TEMPERATURE_FS % % Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default) FREESTREAM_PRESSURE= 101300 % % Free-stream temperature (288.15 K, 518.67 R by default) FREESTREAM_TEMPERATURE= 290 % % Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, % FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) %REF_DIMENSIONALIZATION= DIMENSIONAL % Reynolds number (non-dimensional, based on the free-stream values) %REYNOLDS_NUMBER= 540000 % % Reynolds length (1 m, 1 inch by default) REYNOLDS_LENGTH= 1 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------% % % Navier-Stokes (no-slip), constant heat flux wall marker(s) (NONE = no marker) % Format: ( marker name, constant heat flux (J/m^2), ... ) MARKER_HEATFLUX= ( wall, 0.0 ) % % Symmetry boundary marker(s) (NONE = no marker) MARKER_SYM= ( simmetry ) % % Riemann boundary marker(s) (NONE = no marker) % Format: (marker, data kind flag, list of data) %MARKER_RIEMANN= ( farfield, TOTAL_CONDITIONS_PT, 101300, 298.15, 1.0, 0.0, 0.0, outlet, STATIC_PRESSURE, 100000, 0.0, 0.0, 0.0, 0.0 ) % Inlet boundary marker(s) (NONE = no marker) % Format: ( inlet marker, total temperature, total pressure, flow_direction_x, % flow_direction_y, flow_direction_z, ... ) where flow_direction is % a unit vector. MARKER_INLET= ( farfield, 288.6, 103010.0, 1.0, 0.0, 0.0 ) % % Outlet boundary marker(s) (NONE = no marker) % Format: ( outlet marker, back pressure (static), ... ) MARKER_OUTLET= ( outlet, 101300.0 ) % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% % % Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) NUM_METHOD_GRAD= GREEN_GAUSS % % CFL number (initial value for the adaptive CFL number) CFL_NUMBER= 0.1 % % Adaptive CFL number (NO, YES) %CFL_ADAPT= YES % % Parameters of the adaptive CFL number (factor down, factor up, CFL min value, % CFL max value ) %CFL_ADAPT_PARAM= ( 0.1, 2.0, 10.0, 1000.0 ) % % Maximum Delta Time in local time stepping simulations MAX_DELTA_TIME= 1E6 % ----------- SLOPE LIMITER AND DISSIPATION SENSOR DEFINITION -----------------% % % Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations. % Required for 2nd order upwind schemes (NO, YES) MUSCL_FLOW= YES % % Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG, % BARTH_JESPERSEN, VAN_ALBADA_EDGE) %SLOPE_LIMITER_FLOW= NONE % % Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations. % Required for 2nd order upwind schemes (NO, YES) %MUSCL_TURB= NO % ------------------------ LINEAR SOLVER DEFINITION ---------------------------% % % Linear solver or smoother for implicit formulations (BCGSTAB, FGMRES, SMOOTHER_JACOBI, % SMOOTHER_ILU, SMOOTHER_LUSGS, % SMOOTHER_LINELET) LINEAR_SOLVER= FGMRES % % Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI) LINEAR_SOLVER_PREC= ILU % % Linael solver ILU preconditioner fill-in level (0 by default) LINEAR_SOLVER_ILU_FILL_IN= 0 % % Minimum error of the linear solver for implicit formulations LINEAR_SOLVER_ERROR= 1E-10 % % Max number of iterations of the linear solver for the implicit formulation LINEAR_SOLVER_ITER= 20 % -------------------------- MULTIGRID PARAMETERS -----------------------------% % % Multi-grid levels (0 = no multi-grid) MGLEVEL= 0 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% % % Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, AUSMPLUSUP, AUSMPLUSUP2, HLLC, % TURKEL_PREC, MSW, FDS) CONV_NUM_METHOD_FLOW= ROE % % Entropy fix coefficient (0.0 implies no entropy fixing, 1.0 implies scalar % artificial dissipation) %ENTROPY_FIX_COEFF= 0.1 % % 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 % % Time discretization (EULER_IMPLICIT) TIME_DISCRE_TURB= EULER_IMPLICIT % % Reduction factor of the CFL coefficient in the turbulence problem CFL_REDUCTION_TURB= 1.0 % --------------------------- CONVERGENCE PARAMETERS --------------------------% % Convergence field (see available fields with the -d flag at the command line) %CONV_FIELD= RMS_DENSITY % % Number of total iterations ITER= 5000 % % Min value of the residual (log10 of the residual) CONV_RESIDUAL_MINVAL= -10 % % Start convergence criteria at iteration number CONV_STARTITER= 10 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % % Mesh input file MESH_FILENAME= C_Nozzle_Curve.su2 % % Mesh input file format (SU2, CGNS) MESH_FORMAT= SU2 % % Mesh output file MESH_OUT_FILENAME= mesh_out.su2 % % Restart flow input file SOLUTION_FILENAME= solution_flow.dat % % Output file format (TECPLOT, TECPLOT_BINARY, PARAVIEW, PARAVIEW_BINARY, % FIELDVIEW, FIELDVIEW_BINARY) TABULAR_FORMAT= CSV % % Output file convergence history (w/o extension) CONV_FILENAME= history % % Output file restart flow RESTART_FILENAME= restart_flow.dat % % Output file flow (w/o extension) variables VOLUME_FILENAME= flow % % Output file surface flow coefficient (w/o extension) SURFACE_FILENAME= surface_flow % % Writing solution file frequency OUTPUT_WRT_FREQ= 1000 % % Screen output SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_TKE, RMS_DISSIPATION, LIFT, DRAG) Code:
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % % % SU2 configuration file % % Case description: Supersonic isentropic nozzle flow % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % ------------- 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) SOLVER = EULER % %SOLVER= RANS % % Specify turbulence model (NONE, SA, SA_NEG, SST, SA_E, SA_COMP, SA_E_COMP) %KIND_TURB_MODEL= SA % Mathematical problem (DIRECT, ADJOINT, LINEARIZED) MATH_PROBLEM = DIRECT % Restart solution (NO, YES) RESTART_SOL = NO % -------------------- COMPRESSIBLE FARFIELD DEFINITION --------------------% % Mach number (non-dimensional, based on the free-stream values) MACH_NUMBER = 1.0 % Angle of attack (degrees, only for compressible flows) AOA = 0.0 % Init option to choose between Reynolds (default) or thermodynamics quantities % for initializing the solution (REYNOLDS, TD_CONDITIONS) INIT_OPTION = REYNOLDS % Free-stream option to choose between density and temperature (default) for % initializing the solution (TEMPERATURE_FS, DENSITY_FS) FREESTREAM_OPTION = TEMPERATURE_FS % Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default) FREESTREAM_PRESSURE = 3697978.51402 % Free-stream temperature (288.15 K, 518.67 R by default) FREESTREAM_TEMPERATURE = 3000 % Reynolds length (1 m by default) REYNOLDS_LENGTH = 1.0 % ---------------------- REFERENCE VALUE DEFINITION ---------------------------% % Reference origin for moment computation REF_ORIGIN_MOMENT_X = 0.00 REF_ORIGIN_MOMENT_Y = 0.00 REF_ORIGIN_MOMENT_Z = 0.00 % Reference length for pitching, rolling, and yawing non-dimensional moment REF_LENGTH = 1.0 % Reference area for force coefficients (0 implies automatic calculation) REF_AREA = 0 % ------------------------- IDEAL GAS PROPERTIES -----------------------------% % Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS) FLUID_MODEL = IDEAL_GAS % Ratio of specific heats (1.4 default and the value is hardcoded for the model STANDARD_AIR) GAMMA_VALUE = 1.4 % Specific gas constant (287.058 J/kg*K default, hardcoded for model STANDARD_AIR) GAS_CONSTANT = 287.0 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------% % Euler wall boundary marker(s) (NONE = no marker) MARKER_EULER = ( Nozzle ) % Riemann boundary marker(s) (NONE = no marker) % Format: (marker, data kind flag, list of data) MARKER_RIEMANN= ( Inlet, TOTAL_CONDITIONS_PT, 3697978.51402, 3000, 1.0, 0.0, 0.0, Outlet, STATIC_PRESSURE, 200000.0, 0.0, 0.0, 0.0, 0.0 ) % Farfield marker (NONE = no marker) %MARKER_FAR = ( Inlet ) % Symmetry boundary marker(s) (NONE = no marker) MARKER_SYM = ( Symmetry ) % Supersonic outlet boundary marker(s) (NONE = no marker) %MARKER_SUPERSONIC_OUTLET = ( Outlet ) % ------------------------ SURFACES IDENTIFICATION ----------------------------% % Marker(s) of the surface to be plotted or designed MARKER_PLOTTING = ( Symmetry ) % Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated MARKER_MONITORING = ( Nozzle, Symmetry ) % ------------- 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 = 15 % Adaptive CFL number (NO, YES) %CFL_ADAPT = YES % Parameters of the adaptive CFL number (factor down, factor up, CFL min value, % CFL max value ) CFL_ADAPT_PARAM = ( 0.5, 1.5, 1.0, 100.0 ) % Runge-Kutta alpha coefficients RK_ALPHA_COEFF = ( 0.66667, 0.66667, 1.000000 ) % Number of total iterations ITER = 10000 % OBJECTIVE_FUNCTION= DRAG % ------------------------ LINEAR SOLVER DEFINITION ---------------------------% % Linear solver for implicit formulations (BCGSTAB, FGMRES) LINEAR_SOLVER = FGMRES % Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS) LINEAR_SOLVER_PREC = JACOBI % Minimum error of the linear solver for implicit formulations LINEAR_SOLVER_ERROR = 1E-4 % Max number of iterations of the linear solver for the implicit formulation LINEAR_SOLVER_ITER = 10 % -------------------------- MULTIGRID PARAMETERS -----------------------------% % Multi-Grid Levels (0 = no multi-grid) MGLEVEL = 2 % Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE) MGCYCLE = V_CYCLE % Multi-grid pre-smoothing level MG_PRE_SMOOTH = ( 1, 2, 3, 3 ) % Multi-grid 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 = 0.8 % Damping factor for the correction prolongation MG_DAMP_PROLONGATION = 0.8 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% % Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, % TURKEL_PREC, MSW) CONV_NUM_METHOD_FLOW = JST % % Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations. % Required for 2nd order upwind schemes (NO, YES) MUSCL_FLOW= YES % % Slope limiter (VENKATAKRISHNAN, BARTH_JESPERSEN) SLOPE_LIMITER_FLOW = VENKATAKRISHNAN % Coefficient for the limiter (smooth regions) VENKAT_LIMITER_COEFF = 100.0 % 2nd and 4th order artificial dissipation coefficients JST_SENSOR_COEFF = ( 0.5, 0.02 ) % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) TIME_DISCRE_FLOW = EULER_IMPLICIT % --------------------------- CONVERGENCE PARAMETERS --------------------------% % Convergence criteria (CAUCHY, RESIDUAL) CONV_CRITERIA = RESIDUAL % Min value of the residual (log10 of the residual) CONV_RESIDUAL_MINVAL = -12 % Start convergence criteria at iteration number CONV_STARTITER = 10 % Number of elements to apply the criteria CONV_CAUCHY_ELEMS = 100 % Epsilon to control the series convergence CONV_CAUCHY_EPS = 1E-6 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % Mesh input file MESH_FILENAME = SD_Nozzle_Coarse.su2 %Mesh input file format (SU2, CGNS, NETCDF_ASCII) MESH_FORMAT = SU2 % Mesh output file MESH_OUT_FILENAME = mesh_out.su2 % Restart flow input file SOLUTION_FILENAME = restart.dat % Output file format (CSV, TECPLOT) TABULAR_FORMAT = CSV % Output file convergence history (w/o extension) CONV_FILENAME = history % Output file restart flow RESTART_FILENAME = restart.dat % Output file flow (w/o extension) variables VOLUME_FILENAME = Flow_Sup % Output file surface flow coefficient (w/o extension) SURFACE_FILENAME = surface % Writing solution file frequency OUTPUT_WRT_FREQ = 500 Nicola |
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cfg, nozzle, subsonic, supersonic |
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