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‎design/Inviscid_2D_Unconstrained_NACA0012/inv_NACA0012_basic.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Transonic inviscid optimization of a NACA0012 airfoil %
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% Author: Francisco Palacios %
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% Institution: Stanford University %
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% Date: 2013.09.29 %
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% File Version 5.0.0 "Raven" %
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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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SOLVER= EULER
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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= YES
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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= 0.8
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%
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% Angle of attack (degrees)
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AOA= 1.25
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%
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% Free-stream pressure (101325.0 N/m^2 by default, only Euler flows)
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FREESTREAM_PRESSURE= 101325.0
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%
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% Free-stream temperature (288.15 K by default)
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FREESTREAM_TEMPERATURE= 288.15
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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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% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
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% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
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REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE
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% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
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%
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% Marker of the Euler boundary (0 = no marker)
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MARKER_EULER= ( airfoil )
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%
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% Marker of the far field (0 = no marker)
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MARKER_FAR= ( farfield )
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% ------------------------ SURFACES IDENTIFICATION ----------------------------%
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%
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% Marker of the surface which is going to be plotted or designed
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MARKER_PLOTTING= ( airfoil )
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%
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% Marker 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 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= GREEN_GAUSS
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%
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% Courant-Friedrichs-Lewy condition of the finest grid
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CFL_NUMBER= 10.0
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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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% Number of total iterations
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ITER= 1000
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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% Linear solver for the implicit (or discrete adjoint) formulation (LU_SGS,
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% SYM_GAUSS_SEIDEL, BCGSTAB, GMRES)
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LINEAR_SOLVER= FGMRES
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%
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% Preconditioner of the Krylov linear solver (NONE, JACOBI, LINELET, LUSGS)
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LINEAR_SOLVER_PREC= LU_SGS
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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-4
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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= 2
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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= 2
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%
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% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
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MGCYCLE= V_CYCLE
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%
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% Multi-Grid PreSmoothing Level
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MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
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%
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% Multi-Grid PostSmoothing Level
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MG_POST_SMOOTH= ( 0, 0, 0, 0 )
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%
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% Jacobi implicit smoothing of the correction
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MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
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%
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% Damping factor for the residual restriction
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MG_DAMP_RESTRICTION= 1.0
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%
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% Damping factor for the correction prolongation
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MG_DAMP_PROLONGATION= 1.0
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% --------------------- FLOW NUMERICAL METHOD DEFINITION ----------------------%
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% Convective numerical method (JST, LAX-FRIEDRICH, ROE-1ST_ORDER,
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% ROE-2ND_ORDER)
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CONV_NUM_METHOD_FLOW= JST
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%
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% Slope limiter (VENKATAKRISHNAN)
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SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
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%
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% 2nd and 4th order artificial dissipation coefficients
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JST_SENSOR_COEFF= ( 0.5, 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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% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
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% Adjoint problem boundary condition (DRAG, LIFT, SIDEFORCE, MOMENT_X,
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% MOMENT_Y, MOMENT_Z, EFFICIENCY,
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% EQUIVALENT_AREA, NEARFIELD_PRESSURE,
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% FORCE_X, FORCE_Y, FORCE_Z, THRUST,
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% TORQUE)
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OBJECTIVE_FUNCTION= DRAG
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%
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% Convective numerical method (JST, LAX-FRIEDRICH, ROE-1ST_ORDER,
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% ROE-2ND_ORDER)
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CONV_NUM_METHOD_ADJFLOW= JST
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%
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% Slope limiter (VENKATAKRISHNAN, SHARP_EDGES)
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SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
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%
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% 2nd, and 4th order artificial dissipation coefficients
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ADJ_JST_SENSOR_COEFF= ( 0.0, 0.02 )
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%
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% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT)
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TIME_DISCRE_ADJFLOW= EULER_IMPLICIT
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%
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% Reduction factor of the CFL coefficient in the adjoint problem
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CFL_REDUCTION_ADJFLOW= 0.8
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%
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% Limit value for the adjoint variable
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LIMIT_ADJFLOW= 1E6
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% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------%
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%
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% Marker(s) of the surface where geometrical based function will be evaluated
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GEO_MARKER= ( airfoil )
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%
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% Description of the geometry to be analyzed (AIRFOIL, WING, FUSELAGE)
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GEO_DESCRIPTION= AIRFOIL
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%
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% Geometrical evaluation mode (FUNCTION, GRADIENT)
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GEO_MODE= FUNCTION
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% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
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%
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% Kind of deformation (FFD_SETTING, HICKS_HENNE, HICKS_HENNE_NORMAL, PARABOLIC,
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% HICKS_HENNE_SHOCK, NACA_4DIGITS, DISPLACEMENT, ROTATION,
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% FFD_CONTROL_POINT, FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE,
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% FFD_ROTATION)
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DV_KIND= HICKS_HENNE
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%
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% Marker of the surface in which we are going apply the shape deformation
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DV_MARKER= ( airfoil )
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%
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% Parameters of the shape deformation
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% - HICKS_HENNE_FAMILY ( Lower(0)/Upper(1) side, x_Loc )
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% - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit )
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% - PARABOLIC ( 1st digit, 2nd and 3rd digit )
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% - DISPLACEMENT ( x_Disp, y_Disp, z_Disp )
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% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
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DV_PARAM= ( 1, 0.5 )
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%
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% Value of the shape deformation deformation
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DV_VALUE= 1.0
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% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
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%
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% Number of smoothing iterations for FEA mesh deformation
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DEFORM_LINEAR_SOLVER_ITER= 500
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%
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% Number of nonlinear deformation iterations (surface deformation increments)
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DEFORM_NONLINEAR_ITER= 1
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%
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% Print the residuals during mesh deformation to the console (YES, NO)
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DEFORM_CONSOLE_OUTPUT= YES
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%
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% Minimum residual criteria for the linear solver convergence of grid deformation
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DEFORM_LINEAR_SOLVER_ERROR= 1E-14
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%
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% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME,
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% WALL_DISTANCE, CONSTANT_STIFFNESS)
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DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
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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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%
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -13
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%
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% Start Cauchy criteria at iteration number
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CONV_STARTITER= 10
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%
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% Number of elements to apply the criteria
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CONV_CAUCHY_ELEMS= 100
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%
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% Epsilon to control the series convergence
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CONV_CAUCHY_EPS= 1E-6
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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_inv.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= solution_flow.dat
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%
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% Restart adjoint input file
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SOLUTION_ADJ_FILENAME= solution_adj.dat
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%
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% Output tabular format (CSV, TECPLOT)
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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 adjoint (w/o extension) variables
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VOLUME_ADJ_FILENAME= adjoint
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%
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% Output Objective function gradient (using continuous adjoint)
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GRAD_OBJFUNC_FILENAME= of_grad.dat
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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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% Output file surface adjoint coefficient (w/o extension)
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SURFACE_ADJ_FILENAME= surface_adjoint
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%
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% Writing solution file frequency
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WRT_SOL_FREQ= 250
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%
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% Writing solution file frequency for physical time steps (dual time)
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WRT_SOL_FREQ_DUALTIME= 1
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%
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% Writing convergence history frequency
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WRT_CON_FREQ= 1
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%
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% Writing convergence history frequency (dual time, only written to screen)
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WRT_CON_FREQ_DUALTIME= 10
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%
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% Output rind layers in the solution files
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WRT_HALO= NO
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%
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% Screen output
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SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG)
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% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
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%
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% Available flow based objective functions or constraint functions
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% DRAG, LIFT, SIDEFORCE, EFFICIENCY, BUFFET,
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% FORCE_X, FORCE_Y, FORCE_Z,
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% MOMENT_X, MOMENT_Y, MOMENT_Z,
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% THRUST, TORQUE, FIGURE_OF_MERIT,
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% EQUIVALENT_AREA, NEARFIELD_PRESSURE,
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% TOTAL_HEATFLUX, MAXIMUM_HEATFLUX,
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% INVERSE_DESIGN_PRESSURE, INVERSE_DESIGN_HEATFLUX,
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% SURFACE_TOTAL_PRESSURE, SURFACE_MASSFLOW
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% SURFACE_STATIC_PRESSURE, SURFACE_MACH
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%
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% Available geometrical based objective functions or constraint functions
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% AIRFOIL_AREA, AIRFOIL_THICKNESS, AIRFOIL_CHORD, AIRFOIL_TOC, AIRFOIL_AOA,
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% WING_VOLUME, WING_MIN_THICKNESS, WING_MAX_THICKNESS, WING_MAX_CHORD, WING_MIN_TOC, WING_MAX_TWIST, WING_MAX_CURVATURE, WING_MAX_DIHEDRAL
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% STATION#_WIDTH, STATION#_AREA, STATION#_THICKNESS, STATION#_CHORD, STATION#_TOC,
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% STATION#_TWIST (where # is the index of the station defined in GEO_LOCATION_STATIONS)
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%
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% Available design variables
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% 2D Design variables
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% FFD_CONTROL_POINT_2D ( 19, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, x_Mov, y_Mov )
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% FFD_CAMBER_2D ( 20, Scale | Mark. List | FFD_BoxTag, i_Ind )
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% FFD_THICKNESS_2D ( 21, Scale | Mark. List | FFD_BoxTag, i_Ind )
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% FFD_TWIST_2D ( 22, Scale | Mark. List | FFD_BoxTag, x_Orig, y_Orig )
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% HICKS_HENNE ( 30, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc )
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% ANGLE_OF_ATTACK ( 101, Scale | Mark. List | 1.0 )
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%
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% 3D Design variables
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% FFD_CONTROL_POINT ( 11, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov )
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% FFD_NACELLE ( 12, Scale | Mark. List | FFD_BoxTag, rho_Ind, theta_Ind, phi_Ind, rho_Mov, phi_Mov )
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% FFD_GULL ( 13, Scale | Mark. List | FFD_BoxTag, j_Ind )
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% FFD_CAMBER ( 14, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind )
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% FFD_TWIST ( 15, Scale | Mark. List | FFD_BoxTag, j_Ind, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
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% FFD_THICKNESS ( 16, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind )
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% FFD_ROTATION ( 18, Scale | Mark. List | FFD_BoxTag, x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn )
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% FFD_ANGLE_OF_ATTACK ( 24, Scale | Mark. List | FFD_BoxTag, 1.0 )
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%
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% Global design variables
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% TRANSLATION ( 1, Scale | Mark. List | x_Disp, y_Disp, z_Disp )
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% ROTATION ( 2, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn )
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%
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% Optimization objective function with scaling factor, separated by semicolons.
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% To include quadratic penalty function: use OPT_CONSTRAINT option syntax within the OPT_OBJECTIVE list.
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% ex= Objective * Scale
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OPT_OBJECTIVE= DRAG
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%
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% Optimization constraint functions with pushing factors (affects its value, not the gradient
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% in the python scripts), separated by semicolons
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% ex= (Objective = Value ) * Scale, use '>','<','='
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OPT_CONSTRAINT= NONE
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%
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% Factor to reduce the norm of the gradient (affects the objective function and gradient in the python scripts)
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% In general, a norm of the gradient ~1E-6 is desired.
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OPT_GRADIENT_FACTOR= 1E-6
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%
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% Factor to relax or accelerate the optimizer convergence (affects the line search in SU2_DEF)
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% In general, surface deformations of 0.01'' or 0.0001m are desirable
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OPT_RELAX_FACTOR= 1E3
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%
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% Maximum number of optimizer iterations
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OPT_ITERATIONS= 100
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%
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% Requested accuracy
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OPT_ACCURACY= 1E-10
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%
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% Upper bound for each design variable
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OPT_BOUND_UPPER= 0.1
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%
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% Lower bound for each design variable
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OPT_BOUND_LOWER= -0.1
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%
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% Optimization design variables, separated by semicolons
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DEFINITION_DV= ( 30, 1.0 | airfoil | 0, 0.05 ); ( 30, 1.0 | airfoil | 0, 0.10 ); ( 30, 1.0 | airfoil | 0, 0.15 ); ( 30, 1.0 | airfoil | 0, 0.20 ); ( 30, 1.0 | airfoil | 0, 0.25 ); ( 30, 1.0 | airfoil | 0, 0.30 ); ( 30, 1.0 | airfoil | 0, 0.35 ); ( 30, 1.0 | airfoil | 0, 0.40 ); ( 30, 1.0 | airfoil | 0, 0.45 ); ( 30, 1.0 | airfoil | 0, 0.50 ); ( 30, 1.0 | airfoil | 0, 0.55 ); ( 30, 1.0 | airfoil | 0, 0.60 ); ( 30, 1.0 | airfoil | 0, 0.65 ); ( 30, 1.0 | airfoil | 0, 0.70 ); ( 30, 1.0 | airfoil | 0, 0.75 ); ( 30, 1.0 | airfoil | 0, 0.80 ); ( 30, 1.0 | airfoil | 0, 0.85 ); ( 30, 1.0 | airfoil | 0, 0.90 ); ( 30, 1.0 | airfoil | 0, 0.95 ); ( 30, 1.0 | airfoil | 1, 0.05 ); ( 30, 1.0 | airfoil | 1, 0.10 ); ( 30, 1.0 | airfoil | 1, 0.15 ); ( 30, 1.0 | airfoil | 1, 0.20 ); ( 30, 1.0 | airfoil | 1, 0.25 ); ( 30, 1.0 | airfoil | 1, 0.30 ); ( 30, 1.0 | airfoil | 1, 0.35 ); ( 30, 1.0 | airfoil | 1, 0.40 ); ( 30, 1.0 | airfoil | 1, 0.45 ); ( 30, 1.0 | airfoil | 1, 0.50 ); ( 30, 1.0 | airfoil | 1, 0.55 ); ( 30, 1.0 | airfoil | 1, 0.60 ); ( 30, 1.0 | airfoil | 1, 0.65 ); ( 30, 1.0 | airfoil | 1, 0.70 ); ( 30, 1.0 | airfoil | 1, 0.75 ); ( 30, 1.0 | airfoil | 1, 0.80 ); ( 30, 1.0 | airfoil | 1, 0.85 ); ( 30, 1.0 | airfoil | 1, 0.90 ); ( 30, 1.0 | airfoil | 1, 0.95 )

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