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Merged
pcarruscag merged 4 commits into from
Jan 25, 2021
Merged

update develop #9

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e2132a3
Tutorial files added
Nicola-Fonzi Dec 10, 2020
98e8a00
Modifications as requested by reviewers (#2)
Nicola-Fonzi Dec 16, 2020
a3e5ec9
Merge pull request #8 from su2code/develop
pcarruscag Jan 20, 2021
337a74a
Merge pull request #3 from Nicola-Fonzi/publish
pcarruscag Jan 25, 2021
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210 changes: 210 additions & 0 deletions multiphysics/unsteady_fsi_python/Ma01/fluid.cfg
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Unsteady FSI of a NACA 0012 %
% Author: Nicola Fonzi, Vittorio Cavalieri %
% Institution: Politecnico di Milano %
% Date: Dec 10, 2020 %
% File Version 7.0.8 "Blackbird" (or newer) %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES, NS_PLASMA)
%
SOLVER= RANS
%
% Specify turbulent model (NONE, SA, SA_NEG, SST)
KIND_TURB_MODEL= SST
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
MATH_PROBLEM= DIRECT
%
% ------------------------- UNSTEADY SIMULATION -------------------------------%
%
TIME_DOMAIN = YES
%
% Numerical Method for Unsteady simulation(NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, DUAL_TIME_STEPPING-2ND_ORDER, TIME_SPECTRAL)
TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
%
% Time Step for dual time stepping simulations (s)
TIME_STEP= 1e-3
%
% Maximum Number of physical time steps.
TIME_ITER= 4000
MAX_TIME = 4.0
%
% Number of internal iterations (dual time method)
INNER_ITER= 50
%
% Restart after the transient phase has passed
RESTART_SOL = NO
%
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.1
% Angle of attack (degrees, only for compressible flows)
AOA= 0.0
%
% De-Dimensionalization
REF_DIMENSIONALIZATION = DIMENSIONAL
%
FREESTREAM_TEMPERATURE= 273.0
%
% Reynolds number (non-dimensional, based on the free-stream values)
REYNOLDS_NUMBER= 4e+6
%
% Reynolds length (1 m by default)
REYNOLDS_LENGTH= 1.0
%
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.25
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= 1.0
%
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
% Navier-Stokes wall boundary marker(s) (NONE = no marker)
MARKER_HEATFLUX= ( airfoil, 0.0 )
%
% Farfield boundary marker(s) (NONE = no marker)
MARKER_FAR= ( farfield )
%
% Marker(s) of the surface to be plotted or designed
MARKER_PLOTTING= ( airfoil )
%
% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
MARKER_MONITORING= ( airfoil )
%-------------- Coupling conditions -------------------------------------------%
%
DEFORM_MESH = YES
MARKER_DEFORM_MESH = ( airfoil )
DEFORM_STIFFNESS_TYPE = WALL_DISTANCE
DEFORM_LINEAR_SOLVER_ITER= 200
MARKER_FLUID_LOAD = ( airfoil )
% ------------- 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= 20.0
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= NO
%
% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
% CFL max value )
CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
%
% Runge-Kutta alpha coefficients
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
%
%
% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES
%
% Min error of the linear solver for the implicit formulation
LINEAR_SOLVER_ERROR= 1E-8
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 10
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
% TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= JST
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
% 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, MINMOD)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
JST_SENSOR_COEFF= ( 0.5, 0.01 )
% 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)
%
MUSCL_TURB= NO
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_TURB= EULER_IMPLICIT
%
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
% Convergence criteria (CAUCHY, RESIDUAL)
CONV_CRITERIA = RESIDUAL
% Field to apply Cauchy Criterion to
CONV_FIELD= RMS_DENSITY
% Min value of the residual (log10 of the residual)
CONV_RESIDUAL_MINVAL= -9.0
%
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
%
% Mesh input file
MESH_FILENAME= airfoil.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_flow.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= restart_adj.dat
%
% Output file format (PARAVIEW, TECPLOT, STL)
TABULAR_FORMAT= CSV
%
% Output file convergence history (w/o extension)
CONV_FILENAME= history
%
% Output file restart flow
RESTART_FILENAME= restart_flow.dat
%
% Output file restart adjoint
RESTART_ADJ_FILENAME= restart_adj.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 = 10
%
HISTORY_WRT_FREQ_INNER=1
SCREEN_WRT_FREQ_INNER =1
% Writing convergence history frequency% Writing convergence history frequency (dual time, only written to screen)
HISTORY_WRT_FREQ_TIME=1
SCREEN_WRT_FREQ_TIME =1
%
SCREEN_OUTPUT=(TIME_ITER, INNER_ITER, DRAG, LIFT, RMS_DENSITY, REL_RMS_DENSITY, CAUCHY_TAVG_DRAG, CAUCHY_TAVG_LIFT)
HISTORY_OUTPUT=(ITER,REL_RMS_RES,RMS_RES, AERO_COEFF,TAVG_AERO_COEFF, CAUCHY)
%
37 changes: 37 additions & 0 deletions multiphysics/unsteady_fsi_python/Ma01/fsi.cfg
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Unsteady FSI of a NACA 0012 %
% Author: Nicola Fonzi, Vittorio Cavalieri %
% Institution: Politecnico di Milano %
% Date: Dec 10, 2020 %
% File Version 7.0.8 "Blackbird" (or newer) %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%
% INTEGER VALUES
%%%%%%%%%%%%%%%%%%%%%%%
NDIM = 2
RESTART_ITER = 329
NB_FSI_ITER = 20
%%%%%%%%%%%%%%%%%%%%%%%
% FLOAT VALUES
%%%%%%%%%%%%%%%%%%%%%%%
RBF_RADIUS = 0.5
AITKEN_PARAM = 0.4
UNST_TIMESTEP = 0.001
UNST_TIME = 4.0
TIME_TRESHOLD = 99
FSI_TOLERANCE = 0.000001
%%%%%%%%%%%%%%%%%%%%%%%
% STRING VALUES
%%%%%%%%%%%%%%%%%%%%%%%
CFD_CONFIG_FILE_NAME = fluid.cfg
CSD_SOLVER = AEROELASTIC
CSD_CONFIG_FILE_NAME = solid.cfg
RESTART_SOL = NO
MATCHING_MESH = NO
MESH_INTERP_METHOD = RBF
DISP_PRED = SECOND_ORDER
AITKEN_RELAX = DYNAMIC
TIME_MARCHING = YES
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