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‎multiphysics/unsteady_fsi_python/Ma01/fluid.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Unsteady FSI of a NACA 0012 %
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% Author: Nicola Fonzi, Vittorio Cavalieri %
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% Institution: Politecnico di Milano %
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% Date: Dec 10, 2020 %
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% File Version 7.0.8 "Blackbird" (or newer) %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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% Physical governing equations (EULER, NAVIER_STOKES, NS_PLASMA)
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%
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SOLVER= RANS
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%
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% Specify turbulent model (NONE, SA, SA_NEG, SST)
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KIND_TURB_MODEL= SST
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%
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% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
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MATH_PROBLEM= DIRECT
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%
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% ------------------------- UNSTEADY SIMULATION -------------------------------%
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%
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TIME_DOMAIN = YES
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%
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% Numerical Method for Unsteady simulation(NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, DUAL_TIME_STEPPING-2ND_ORDER, TIME_SPECTRAL)
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TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
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%
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% Time Step for dual time stepping simulations (s)
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TIME_STEP= 1e-3
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%
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% Maximum Number of physical time steps.
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TIME_ITER= 4000
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MAX_TIME = 4.0
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%
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% Number of internal iterations (dual time method)
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INNER_ITER= 50
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%
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% Restart after the transient phase has passed
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RESTART_SOL = NO
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%
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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% Mach number (non-dimensional, based on the free-stream values)
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MACH_NUMBER= 0.1
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% Angle of attack (degrees, only for compressible flows)
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AOA= 0.0
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%
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% De-Dimensionalization
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REF_DIMENSIONALIZATION = DIMENSIONAL
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%
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FREESTREAM_TEMPERATURE= 273.0
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%
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% Reynolds number (non-dimensional, based on the free-stream values)
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REYNOLDS_NUMBER= 4e+6
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%
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% Reynolds length (1 m by default)
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REYNOLDS_LENGTH= 1.0
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%
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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% Reference origin for moment computation
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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%
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% Reference length for pitching, rolling, and yawing non-dimensional moment
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REF_LENGTH= 1.0
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%
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% Reference area for force coefficients (0 implies automatic calculation)
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REF_AREA= 1.0
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%
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Navier-Stokes wall boundary marker(s) (NONE = no marker)
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MARKER_HEATFLUX= ( airfoil, 0.0 )
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%
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% Farfield boundary marker(s) (NONE = no marker)
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MARKER_FAR= ( farfield )
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%
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% Marker(s) of the surface to be plotted or designed
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MARKER_PLOTTING= ( airfoil )
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%
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% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
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MARKER_MONITORING= ( airfoil )
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%-------------- Coupling conditions -------------------------------------------%
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%
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DEFORM_MESH = YES
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MARKER_DEFORM_MESH = ( airfoil )
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DEFORM_STIFFNESS_TYPE = WALL_DISTANCE
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DEFORM_LINEAR_SOLVER_ITER= 200
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MARKER_FLUID_LOAD = ( airfoil )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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%
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% Courant-Friedrichs-Lewy condition of the finest grid
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CFL_NUMBER= 20.0
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%
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% Adaptive CFL number (NO, YES)
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CFL_ADAPT= NO
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%
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% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
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% CFL max value )
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CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
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%
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% Runge-Kutta alpha coefficients
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RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
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%
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%
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% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
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LINEAR_SOLVER= FGMRES
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%
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% Min error of the linear solver for the implicit formulation
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LINEAR_SOLVER_ERROR= 1E-8
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%
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% Max number of iterations of the linear solver for the implicit formulation
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LINEAR_SOLVER_ITER= 10
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%
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
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% TURKEL_PREC, MSW)
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CONV_NUM_METHOD_FLOW= JST
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%
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% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
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%
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% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations.
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% Required for 2nd order upwind schemes (NO, YES)
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MUSCL_FLOW= YES
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% Slope limiter (VENKATAKRISHNAN, MINMOD)
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SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
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%
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JST_SENSOR_COEFF= ( 0.5, 0.01 )
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% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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%
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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% Convective numerical method (SCALAR_UPWIND)
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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%
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% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
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%
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MUSCL_TURB= NO
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SLOPE_LIMITER_TURB= VENKATAKRISHNAN
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%
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% Time discretization (EULER_IMPLICIT)
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TIME_DISCRE_TURB= EULER_IMPLICIT
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%
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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% Convergence criteria (CAUCHY, RESIDUAL)
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CONV_CRITERIA = RESIDUAL
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% Field to apply Cauchy Criterion to
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CONV_FIELD= RMS_DENSITY
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -9.0
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%
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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%
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% Mesh input file
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MESH_FILENAME= airfoil.su2
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%
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% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
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MESH_FORMAT= SU2
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%
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% Mesh output file
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MESH_OUT_FILENAME= mesh_out.su2
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%
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% Restart flow input file
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SOLUTION_FILENAME= restart_flow.dat
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%
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% Restart adjoint input file
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SOLUTION_ADJ_FILENAME= restart_adj.dat
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%
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% Output file format (PARAVIEW, TECPLOT, STL)
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TABULAR_FORMAT= CSV
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%
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% Output file convergence history (w/o extension)
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CONV_FILENAME= history
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%
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% Output file restart flow
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RESTART_FILENAME= restart_flow.dat
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%
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% Output file restart adjoint
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RESTART_ADJ_FILENAME= restart_adj.dat
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%
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% Output file flow (w/o extension) variables
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VOLUME_FILENAME= flow
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%
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% Output file surface flow coefficient (w/o extension)
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SURFACE_FILENAME= surface_flow
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%
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% Writing solution file frequency
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OUTPUT_WRT_FREQ = 10
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%
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HISTORY_WRT_FREQ_INNER=1
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SCREEN_WRT_FREQ_INNER =1
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% Writing convergence history frequency% Writing convergence history frequency (dual time, only written to screen)
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HISTORY_WRT_FREQ_TIME=1
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SCREEN_WRT_FREQ_TIME =1
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%
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SCREEN_OUTPUT=(TIME_ITER, INNER_ITER, DRAG, LIFT, RMS_DENSITY, REL_RMS_DENSITY, CAUCHY_TAVG_DRAG, CAUCHY_TAVG_LIFT)
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HISTORY_OUTPUT=(ITER,REL_RMS_RES,RMS_RES, AERO_COEFF,TAVG_AERO_COEFF, CAUCHY)
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%

‎multiphysics/unsteady_fsi_python/Ma01/fsi.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Unsteady FSI of a NACA 0012 %
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% Author: Nicola Fonzi, Vittorio Cavalieri %
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% Institution: Politecnico di Milano %
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% Date: Dec 10, 2020 %
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% File Version 7.0.8 "Blackbird" (or newer) %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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%%%%%%%%%%%%%%%%%%%%%%%
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% INTEGER VALUES
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%%%%%%%%%%%%%%%%%%%%%%%
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NDIM = 2
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RESTART_ITER = 329
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NB_FSI_ITER = 20
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%%%%%%%%%%%%%%%%%%%%%%%
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% FLOAT VALUES
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%%%%%%%%%%%%%%%%%%%%%%%
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RBF_RADIUS = 0.5
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AITKEN_PARAM = 0.4
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UNST_TIMESTEP = 0.001
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UNST_TIME = 4.0
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TIME_TRESHOLD = 99
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FSI_TOLERANCE = 0.000001
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%%%%%%%%%%%%%%%%%%%%%%%
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% STRING VALUES
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%%%%%%%%%%%%%%%%%%%%%%%
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CFD_CONFIG_FILE_NAME = fluid.cfg
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CSD_SOLVER = AEROELASTIC
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CSD_CONFIG_FILE_NAME = solid.cfg
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RESTART_SOL = NO
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MATCHING_MESH = NO
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MESH_INTERP_METHOD = RBF
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DISP_PRED = SECOND_ORDER
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AITKEN_RELAX = DYNAMIC
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TIME_MARCHING = YES

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