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‎Inc_Inviscid_Hydrofoil/images/hydrofoil_pressure.png‎

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‎Inc_Inviscid_Hydrofoil/inv_naca0012.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Incompressible flow hydrofoil 5 degrees %
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% Author: Francisco Palacios & Thomas D. Economon %
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% Date: 6.10.2018 %
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% File Version 6.1.0 "Falcon" %
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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,
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% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
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% POISSON_EQUATION)
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PHYSICAL_PROBLEM= EULER
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%
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% Regime type (COMPRESSIBLE, INCOMPRESSIBLE)
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REGIME_TYPE= INCOMPRESSIBLE
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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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% Restart solution (NO, YES)
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RESTART_SOL= NO
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% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
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%
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% Initial density for incompressible flows
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% (1.2886 kg/m^3 by default (air), 998.2 Kg/m^3 (water))
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INC_DENSITY_INIT= 998.2
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%
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% Initial velocity for incompressible flows (1.0,0,0 m/s by default)
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INC_VELOCITY_INIT= ( 1.775, 0.0, 0.0 )
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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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% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
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%
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% Euler wall boundary marker(s) (NONE = no marker)
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MARKER_EULER= ( airfoil, lower_wall, upper_wall )
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%
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% Inlet boundary marker(s) with the following formats (NONE = no marker)
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% Incompressible: (inlet marker, temperature, velocity magnitude, flow_direction_x,
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% flow_direction_y, flow_direction_z, ... ) where flow_direction is
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% a unit vector.
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MARKER_INLET= ( inlet, 0.0, 1.775, 1.0, 0.0, 0.0 )
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%
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% Outlet boundary marker(s) (NONE = no marker)
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MARKER_OUTLET= ( outlet, 0.0 )
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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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% ------------- COMMON PARAMETERS TO DEFINE 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= GREEN_GAUSS
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%
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% Courant-Friedrichs-Lewy condition of the finest grid
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CFL_NUMBER= 1e6
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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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% Number of total iterations
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EXT_ITER= 9999
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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% Linear solver or smoother for implicit formulations (BCGSTAB, FGMRES, SMOOTHER_JACOBI,
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% SMOOTHER_ILU, SMOOTHER_LUSGS,
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% SMOOTHER_LINELET)
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LINEAR_SOLVER= FGMRES
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%
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% Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI)
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LINEAR_SOLVER_PREC= ILU
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%
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% Linael solver ILU preconditioner fill-in level (0 by default)
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LINEAR_SOLVER_ILU_FILL_IN= 0
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%
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% Minimum error of the linear solver for implicit formulations
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LINEAR_SOLVER_ERROR= 1E-15
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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= 25
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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%
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% Multi-Grid Levels (0 = no multi-grid)
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MGLEVEL= 0
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%
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% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
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MGCYCLE= W_CYCLE
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%
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% Multi-grid pre-smoothing level
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MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
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%
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% Multi-grid post-smoothing level
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MG_POST_SMOOTH= ( 1, 1, 1, 1 )
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%
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% Jacobi implicit smoothing of the correction
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MG_CORRECTION_SMOOTH= ( 1, 1, 1, 1 )
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%
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% Damping factor for the residual restriction
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MG_DAMP_RESTRICTION= 0.85
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%
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% Damping factor for the correction prolongation
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MG_DAMP_PROLONGATION= 0.85
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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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% 2nd and 4th order artificial dissipation coefficients
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JST_SENSOR_COEFF= ( 0.0, 0.02 )
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%
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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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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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% Convergence criteria (CAUCHY, RESIDUAL)
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%
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CONV_CRITERIA= RESIDUAL
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%
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% Residual reduction (order of magnitude with respect to the initial value)
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RESIDUAL_REDUCTION= 10
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%
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% Min value of the residual (log10 of the residual)
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RESIDUAL_MINVAL= -18
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%
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% Start Cauchy criteria at iteration number
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STARTCONV_ITER= 10
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%
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% Number of elements to apply the criteria
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CAUCHY_ELEMS= 50
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%
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% Epsilon to control the series convergence
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CAUCHY_EPS= 1E-6
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%
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% Function to apply the criteria (LIFT, DRAG, SENS_GEOMETRY, SENS_MACH,
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% DELTA_LIFT, DELTA_DRAG)
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CAUCHY_FUNC_FLOW= DRAG
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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% Mesh input file
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MESH_FILENAME= mesh_NACA0012_5deg_6814.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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% Restart flow input file
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SOLUTION_FLOW_FILENAME= solution_flow.dat
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%
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% Output file format (PARAVIEW, TECPLOT)
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OUTPUT_FORMAT= PARAVIEW
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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_FLOW_FILENAME= restart_flow.dat
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%
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% Output file flow (w/o extension) variables
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VOLUME_FLOW_FILENAME= flow
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%
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% Output file surface flow coefficient (w/o extension)
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SURFACE_FLOW_FILENAME= surface_flow
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%
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% Writing solution file frequency
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WRT_SOL_FREQ= 50
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%
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% Writing convergence history frequency
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WRT_CON_FREQ= 1

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