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Copy pathinv_adj_NACA0012.cfg
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135 lines (103 loc) · 5.45 KB
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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 7.5.1 "Blackbird" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
SOLVER= EULER
MATH_PROBLEM= CONTINUOUS_ADJOINT
RESTART_SOL= NO
% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
MACH_NUMBER= 0.8
AOA= 1.25
FREESTREAM_PRESSURE= 101325.0
FREESTREAM_TEMPERATURE= 273.15
% -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------%
GAMMA_VALUE= 1.4
GAS_CONSTANT= 287.87
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
REF_LENGTH= 1.0
REF_AREA= 1.0
REF_DIMENSIONALIZATION= DIMENSIONAL
% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
MARKER_EULER= ( airfoil )
MARKER_FAR= ( farfield )
% ------------------------ SURFACES IDENTIFICATION ----------------------------%
MARKER_PLOTTING = ( airfoil )
MARKER_MONITORING = ( airfoil )
MARKER_DESIGNING = ( airfoil )
% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
OBJECTIVE_FUNCTION= DRAG
CFL_NUMBER= 1e3
CFL_ADAPT= NO
CFL_ADAPT_PARAM= ( 0.1, 2.0, 10.0, 1e10 )
ITER= 250
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
LINEAR_SOLVER= FGMRES
LINEAR_SOLVER_PREC= ILU
LINEAR_SOLVER_ERROR= 1E-10
LINEAR_SOLVER_ITER= 10
% -------------------------- MULTIGRID PARAMETERS -----------------------------%
MGLEVEL= 3
MGCYCLE= W_CYCLE
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
MG_DAMP_RESTRICTION= 1.0
MG_DAMP_PROLONGATION= 1.0
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
CONV_NUM_METHOD_FLOW= JST
JST_SENSOR_COEFF= ( 0.5, 0.02 )
TIME_DISCRE_FLOW= EULER_IMPLICIT
% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
CONV_NUM_METHOD_ADJFLOW= JST
CFL_REDUCTION_ADJFLOW= 0.01
TIME_DISCRE_ADJFLOW= EULER_IMPLICIT
% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
DV_KIND= HICKS_HENNE
DV_MARKER= ( airfoil )
DV_PARAM= ( 1, 0.5 )
DV_VALUE= 0.01
% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
DEFORM_LINEAR_SOLVER_ITER= 500
DEFORM_NONLINEAR_ITER= 1
DEFORM_LINEAR_SOLVER_ERROR= 1E-14
DEFORM_CONSOLE_OUTPUT= YES
DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
CONV_FIELD= RMS_DENSITY
CONV_RESIDUAL_MINVAL= -8
CONV_STARTITER= 10
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-6
SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_RES, LIFT, DRAG, CAUCHY_SENS_PRESS, CAUCHY_DRAG RMS_ADJ_DENSITY RMS_ADJ_ENERGY)
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
MESH_FILENAME= mesh_NACA0012_inv.su2
MESH_FORMAT= SU2
MESH_OUT_FILENAME= mesh_out.su2
SOLUTION_FILENAME= solution_flow
SOLUTION_ADJ_FILENAME= solution_adj
TABULAR_FORMAT= CSV
CONV_FILENAME= history
RESTART_FILENAME= restart_flow
RESTART_ADJ_FILENAME= restart_adj
VOLUME_FILENAME= flow
VOLUME_ADJ_FILENAME= adjoint
GRAD_OBJFUNC_FILENAME= of_grad.dat
SURFACE_FILENAME= surface_flow
SURFACE_ADJ_FILENAME= surface_adjoint
OUTPUT_WRT_FREQ= 250
OUTPUT_FILES= (RESTART, SURFACE_CSV)
% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
OPT_OBJECTIVE= DRAG * 0.001
OPT_CONSTRAINT= ( LIFT > 0.328188 ) * 0.001; ( MOMENT_Z > 0.034068 ) * 0.001; ( AIRFOIL_THICKNESS > 0.11 ) * 0.001
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 )