Added quick start

QuickStart/inv_NACA0012.cfg

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+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                              %
+% SU2 configuration file                                                       %
+% Case description: Transonic inviscid flow around a NACA0012 airfoil          %
+% Author: Thomas D. Economon                                                   %
+% Institution: Stanford University                                             %
+% Date: 2014.06.11                                                             %
+% File Version 3.2.0 "eagle"                                                   %
+%                                                                              %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+% ------------- 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)
+PHYSICAL_PROBLEM= EULER
+%
+% Mathematical problem (DIRECT, ADJOINT)
+MATH_PROBLEM= DIRECT
+%
+% Restart solution (NO, YES)
+RESTART_SOL= NO
+
+% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
+%
+% Mach number (non-dimensional, based on the free-stream values)
+MACH_NUMBER= 0.8
+%
+% Angle of attack (degrees)
+AoA= 1.25
+%
+% Free-stream pressure (101325.0 N/m^2 by default, only Euler flows)  
+FREESTREAM_PRESSURE= 101325.0
+%
+% Free-stream temperature (273.15 K by default)
+FREESTREAM_TEMPERATURE= 273.15
+
+% -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------%
+%
+% Ratio of specific heats (1.4 (air), only for compressible flows)
+GAMMA_VALUE= 1.4
+%
+% Specific gas constant (287.87 J/kg*K (air), only for compressible flows)
+GAS_CONSTANT= 287.87
+
+% ---------------------- 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_MOMENT= 1.0
+%
+% Reference area for force coefficients (0 implies automatic calculation)
+REF_AREA= 1.0
+%
+% Reference pressure (101325.0 N/m^2 by default)
+REF_PRESSURE= 1.0
+%
+% Reference temperature (273.15 K by default)
+REF_TEMPERATURE= 1.0
+%
+% Reference density (1.2886 Kg/m^3 (air), 998.2 Kg/m^3 (water)) 
+REF_DENSITY= 1.0
+
+% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
+%
+% Marker of the Euler boundary (NONE = no marker)
+MARKER_EULER= ( airfoil )
+%
+% Marker of the far field (NONE = no marker)
+MARKER_FAR= ( farfield )
+
+% ------------------------ SURFACES IDENTIFICATION ----------------------------%
+%
+% Marker(s) of the surface in the surface flow solution file
+MARKER_PLOTTING = ( airfoil )
+%
+% Marker(s) of the surface where the non-dimensional coefficients are evaluated.
+MARKER_MONITORING = ( airfoil )
+%
+% Marker(s) of the surface where obj. func. (design problem) will be evaluated
+MARKER_DESIGNING = ( airfoil )
+
+% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
+%
+% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
+NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
+%
+% Objective function in optimization problem (DRAG, LIFT, SIDEFORCE, MOMENT_X,
+%                                             MOMENT_Y, MOMENT_Z, EFFICIENCY,
+%                                             EQUIVALENT_AREA, NEARFIELD_PRESSURE,
+%                                             FORCE_X, FORCE_Y, FORCE_Z, THRUST,
+%                                             TORQUE, FREE_SURFACE, TOTAL_HEATFLUX,
+%                                             MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE,
+%                                             INVERSE_DESIGN_HEATFLUX)
+OBJECTIVE_FUNCTION= DRAG
+%
+% Courant-Friedrichs-Lewy condition of the finest grid
+CFL_NUMBER= 4.0
+%
+% CFL ramp (factor, number of iterations, CFL limit)
+CFL_RAMP= ( 1.0, 100, 1.0 )
+%
+% Number of total iterations
+EXT_ITER= 250
+
+% ------------------------ 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= LU_SGS
+%
+% Minimum error of the linear solver for implicit formulations
+LINEAR_SOLVER_ERROR= 1E-6
+%
+% Max number of iterations of the linear solver for the implicit formulation
+LINEAR_SOLVER_ITER= 5
+%
+% Relaxation coefficient
+LINEAR_SOLVER_RELAX= 1.0
+
+% -------------------------- MULTIGRID PARAMETERS -----------------------------%
+%
+% Multi-Grid Levels (0 = no multi-grid)
+MGLEVEL= 3
+%
+% Multi-Grid Cycle (0 = V cycle, 1 = W Cycle)
+MGCYCLE= 1
+%
+% Reduction factor of the CFL coefficient on the coarse levels
+MG_CFL_REDUCTION= 0.9
+%
+% Maximum number of children in the agglomeration stage
+MAX_CHILDREN= 250
+%
+% Maximum length of an agglomerated element (compared with the domain)
+MAX_DIMENSION= 0.1
+%
+% Multi-Grid PreSmoothing Level
+MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
+%
+% Multi-Grid PostSmoothing 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= 1.0
+%
+% Damping factor for the correction prolongation
+MG_DAMP_PROLONGATION= 1.0
+
+% -------------------- 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)
+%
+SPATIAL_ORDER_FLOW= 2ND_ORDER_LIMITER
+%
+% Slope limiter (VENKATAKRISHNAN, MINMOD)
+SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
+%
+% 1st, 2nd and 4th order artificial dissipation coefficients
+AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 )
+%
+% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
+TIME_DISCRE_FLOW= EULER_IMPLICIT
+
+% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
+%
+% Convective numerical method (JST, LAX-FRIEDRICH, ROE)
+CONV_NUM_METHOD_ADJFLOW= JST
+%
+% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
+%
+SPATIAL_ORDER_ADJFLOW= 2ND_ORDER
+%
+% Slope limiter (VENKATAKRISHNAN, SHARP_EDGES)
+SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
+%
+% 1st, 2nd, and 4th order artificial dissipation coefficients
+AD_COEFF_ADJFLOW= ( 0.15, 0.5, 0.02 )
+%
+% Reduction factor of the CFL coefficient in the adjoint problem
+CFL_REDUCTION_ADJFLOW= 0.5
+%
+% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT)
+TIME_DISCRE_ADJFLOW= EULER_IMPLICIT
+
+% --------------------------- PARTITIONING STRATEGY ---------------------------%
+% Write a paraview file for each partition (NO, YES)
+VISUALIZE_PART= NO
+
+% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
+%
+% Kind of deformation (FFD_SETTING, FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D,
+%                      HICKS_HENNE, COSINE_BUMP, PARABOLIC,
+%                      NACA_4DIGITS, DISPLACEMENT, ROTATION, FFD_CONTROL_POINT, 
+%                      FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE, FFD_ROTATION,
+%                      FFD_CAMBER, FFD_THICKNESS, SURFACE_FILE, AIRFOIL)
+DV_KIND= HICKS_HENNE 
+%
+% Marker of the surface in which we are going apply the shape deformation
+DV_MARKER= ( airfoil )
+%
+% Parameters of the shape deformation
+% - FFD_CONTROL_POINT_2D ( FFD_Box_ID, i_Ind, j_Ind, x_Disp, y_Disp )
+% - FFD_CAMBER_2D ( FFD_Box_ID, i_Ind )
+% - FFD_THICKNESS_2D ( FFD_Box_ID, i_Ind )
+% - HICKS_HENNE ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc )
+% - COSINE_BUMP ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc, x_Size )
+% - FOURIER ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), index, cos(0)/sin(1) )
+% - SPHERICAL ( ControlPoint_Index, Theta_Disp, R_Disp )
+% - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit )
+% - PARABOLIC ( Center, Thickness )
+% - DISPLACEMENT ( x_Disp, y_Disp, z_Disp )
+% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
+% - OBSTACLE ( Center, Bump size )
+DV_PARAM= ( 1, 0.5 )
+%
+% Value of the shape deformation
+DV_VALUE= 0.01
+%
+% Surface deformation input filename (SURFACE_FILE DV only)
+MOTION_FILENAME= mesh_motion.dat
+
+% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
+%
+% Number of smoothing iterations for FEA mesh deformation
+DEFORM_LINEAR_ITER= 500
+%
+% Number of nonlinear deformation iterations (surface deformation increments)
+DEFORM_NONLINEAR_ITER= 1
+%
+% Print the residuals during mesh deformation to the console (YES, NO)
+DEFORM_CONSOLE_OUTPUT= YES
+%
+% Factor to multiply smallest cell volume for deform tolerance (0.001 default)
+DEFORM_TOL_FACTOR = 0.001
+%
+% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME, 
+%                                          WALL_DISTANCE, CONSTANT_STIFFNESS)
+DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
+%
+% Visualize the deformation (NO, YES)
+VISUALIZE_DEFORMATION= NO
+%
+% Divide elements into triangles and tetrahedra (NO, YES)
+DIVIDE_ELEMENTS= NO
+
+% --------------------------- CONVERGENCE PARAMETERS --------------------------%
+% Convergence criteria (CAUCHY, RESIDUAL)
+%
+CONV_CRITERIA= CAUCHY
+%
+% Residual reduction (order of magnitude with respect to the initial value)
+RESIDUAL_REDUCTION= 6
+%
+% Min value of the residual (log10 of the residual)
+RESIDUAL_MINVAL= -8
+%
+% Start Cauchy criteria at iteration number
+STARTCONV_ITER= 10
+%
+% Number of elements to apply the criteria
+CAUCHY_ELEMS= 100
+%
+% Epsilon to control the series convergence
+CAUCHY_EPS= 1E-6
+%
+% Function to apply the criteria (LIFT, DRAG, SENS_GEOMETRY, SENS_MACH,
+%                                 DELTA_LIFT, DELTA_DRAG)
+CAUCHY_FUNC_FLOW= DRAG
+
+% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
+% Mesh input file
+MESH_FILENAME= mesh_NACA0012_inv.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_FLOW_FILENAME= solution_flow.dat
+%
+% Restart adjoint input file
+SOLUTION_ADJ_FILENAME= solution_adj.dat
+%
+% Output file format (TECPLOT, PARAVIEW, TECPLOT_BINARY)
+OUTPUT_FORMAT= TECPLOT
+%
+% Output file convergence history (w/o extension) 
+CONV_FILENAME= history
+%
+% Output file restart flow
+RESTART_FLOW_FILENAME= restart_flow.dat
+%
+% Output file restart adjoint
+RESTART_ADJ_FILENAME= restart_adj.dat
+%
+% Output file flow (w/o extension) variables
+VOLUME_FLOW_FILENAME= flow
+%
+% Output file adjoint (w/o extension) variables
+VOLUME_ADJ_FILENAME= adjoint
+%
+% Output Objective function gradient (using continuous adjoint)
+GRAD_OBJFUNC_FILENAME= of_grad.dat
+%
+% Output file surface flow coefficient (w/o extension)
+SURFACE_FLOW_FILENAME= surface_flow
+%
+% Output file surface adjoint coefficient (w/o extension)
+SURFACE_ADJ_FILENAME= surface_adjoint
+%
+% Writing solution file frequency
+WRT_SOL_FREQ= 250
+%
+% Writing convergence history frequency
+WRT_CON_FREQ= 1
+
+% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
+% Available flow based objective functions or constraint functions
+%    DRAG, LIFT, SIDEFORCE, EFFICIENCY,
+%    FORCE_X, FORCE_Y, FORCE_Z,
+%    MOMENT_X, MOMENT_Y, MOMENT_Z,
+%    THRUST, TORQUE, FIGURE_OF_MERIT,
+%    EQUIVALENT_AREA, NEARFIELD_PRESSURE, 
+%    TOTAL_HEATFLUX, MAXIMUM_HEATFLUX,
+%    INVERSE_DESIGN_PRESSURE, INVERSE_DESIGN_HEATFLUX,
+%    FREE_SURFACE
+%
+% Available geometrical based objective functions or constraint functions
+%    MAX_THICKNESS, 1/4_THICKNESS, 1/2_THICKNESS, 3/4_THICKNESS, AREA, AOA, CHORD, 
+%    MAX_THICKNESS_SEC1, MAX_THICKNESS_SEC2, MAX_THICKNESS_SEC3, MAX_THICKNESS_SEC4, MAX_THICKNESS_SEC5, 
+%    1/4_THICKNESS_SEC1, 1/4_THICKNESS_SEC2, 1/4_THICKNESS_SEC3, 1/4_THICKNESS_SEC4, 1/4_THICKNESS_SEC5, 
+%    1/2_THICKNESS_SEC1, 1/2_THICKNESS_SEC2, 1/2_THICKNESS_SEC3, 1/2_THICKNESS_SEC4, 1/2_THICKNESS_SEC5, 
+%    3/4_THICKNESS_SEC1, 3/4_THICKNESS_SEC2, 3/4_THICKNESS_SEC3, 3/4_THICKNESS_SEC4, 3/4_THICKNESS_SEC5, 
+%    AREA_SEC1, AREA_SEC2, AREA_SEC3, AREA_SEC4, AREA_SEC5, 
+%    AOA_SEC1, AOA_SEC2, AOA_SEC3, AOA_SEC4, AOA_SEC5, 
+%    CHORD_SEC1, CHORD_SEC2, CHORD_SEC3, CHORD_SEC4, CHORD_SEC5
+%
+% Available design variables
+%    HICKS_HENNE 	(  1, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc )
+%    COSINE_BUMP	(  2, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc, x_Size )
+%    SPHERICAL		(  3, Scale | Mark. List | ControlPoint_Index, Theta_Disp, R_Disp )
+%    NACA_4DIGITS	(  4, Scale | Mark. List | 1st digit, 2nd digit, 3rd and 4th digit )
+%    DISPLACEMENT	(  5, Scale | Mark. List | x_Disp, y_Disp, z_Disp )
+%    ROTATION		(  6, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn )
+%    FOURIER 		( 14, Scale | Mark. List | Lower(0)/Upper(1) side, index, cos(0)/sin(1) )
+%    FFD_CONTROL_POINT_2D (  15, Scale | Mark. List | FFD_Box_ID, i_Ind, j_Ind, x_Mov, y_Mov )
+%    FFD_CAMBER_2D 	( 16, Scale | Mark. List | FFD_Box_ID, i_Ind )
+%    FFD_THICKNESS_2D 	( 17, Scale | Mark. List | FFD_Box_ID, i_Ind )
+%
+% Optimization objective function with scaling factor
+% ex= Objective * Scale
+OPT_OBJECTIVE= DRAG * 0.001
+%
+% Optimization constraint functions with scaling factors, separated by semicolons
+% ex= (Objective = Value ) * Scale, use '>','<','='
+OPT_CONSTRAINT= ( LIFT > 0.328188 ) * 0.001; ( MOMENT_Z > 0.034068 ) * 0.001; ( MAX_THICKNESS > 0.11 ) * 0.001
+%
+% Optimization design variables, separated by semicolons
+DEFINITION_DV= ( 1, 1.0 | airfoil | 0, 0.05 ); ( 1, 1.0 | airfoil | 0, 0.10 ); ( 1, 1.0 | airfoil | 0, 0.15 ); ( 1, 1.0 | airfoil | 0, 0.20 ); ( 1, 1.0 | airfoil | 0, 0.25 ); ( 1, 1.0 | airfoil | 0, 0.30 ); ( 1, 1.0 | airfoil | 0, 0.35 ); ( 1, 1.0 | airfoil | 0, 0.40 ); ( 1, 1.0 | airfoil | 0, 0.45 ); ( 1, 1.0 | airfoil | 0, 0.50 ); ( 1, 1.0 | airfoil | 0, 0.55 ); ( 1, 1.0 | airfoil | 0, 0.60 ); ( 1, 1.0 | airfoil | 0, 0.65 ); ( 1, 1.0 | airfoil | 0, 0.70 ); ( 1, 1.0 | airfoil | 0, 0.75 ); ( 1, 1.0 | airfoil | 0, 0.80 ); ( 1, 1.0 | airfoil | 0, 0.85 ); ( 1, 1.0 | airfoil | 0, 0.90 ); ( 1, 1.0 | airfoil | 0, 0.95 ); ( 1, 1.0 | airfoil | 1, 0.05 ); ( 1, 1.0 | airfoil | 1, 0.10 ); ( 1, 1.0 | airfoil | 1, 0.15 ); ( 1, 1.0 | airfoil | 1, 0.20 ); ( 1, 1.0 | airfoil | 1, 0.25 ); ( 1, 1.0 | airfoil | 1, 0.30 ); ( 1, 1.0 | airfoil | 1, 0.35 ); ( 1, 1.0 | airfoil | 1, 0.40 ); ( 1, 1.0 | airfoil | 1, 0.45 ); ( 1, 1.0 | airfoil | 1, 0.50 ); ( 1, 1.0 | airfoil | 1, 0.55 ); ( 1, 1.0 | airfoil | 1, 0.60 ); ( 1, 1.0 | airfoil | 1, 0.65 ); ( 1, 1.0 | airfoil | 1, 0.70 ); ( 1, 1.0 | airfoil | 1, 0.75 ); ( 1, 1.0 | airfoil | 1, 0.80 ); ( 1, 1.0 | airfoil | 1, 0.85 ); ( 1, 1.0 | airfoil | 1, 0.90 ); ( 1, 1.0 | airfoil | 1, 0.95 )