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Does anyone knows what does this error "Inequality constraints incompatible" mean? |
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Does anyone knows what does this error "Inequality constraints incompatible" mean? I am running Unconstrained shape design of a transonic inviscid airfoil with drag minimization as objective function
Output: NIT FC OBJFUN GNORM 1 2 1.023599E-07 4.329394E-06 2 3 4.859100E-08 3.928248E-06 3 4 5.061749E-08 4.935224E-06 4 6 6.119141E-08 4.595797E-06 5 8 7.981814E-08 4.238165E-06 6 10 1.129311E-07 3.852231E-06 7 13 1.117234E-07 3.803846E-06 8 15 4.570094E-08 3.379758E-06 9 17 4.655308E-08 2.793967E-06 10 19 4.698743E-08 2.611147E-06 11 21 5.238096E-07 2.170625E-06 12 24 8.917623E-07 2.801978E-06 13 28 8.978185E-07 3.273778E-06 14 32 9.049461E-07 3.798185E-06 15 36 9.000981E-07 4.480434E-06 16 40 8.950473E-07 5.361226E-06 17 44 9.052266E-07 6.648547E-06 18 48 9.058547E-07 9.442393E-06 19 52 -8.117720E-01 2.242141E-05 20 52 -8.117720E-01 7.129478E+05 Inequality constraints incompatible (Exit mode 4) Current function value: -0.8117719632999999 Iterations: 20 Function evaluations: 52 Gradient evaluations: 20 PS D:\SU2\Tutorials-master\design\Project Graph\Inviscid_2D_Unconstrained_NACA0012 fM0.86 vAOA3.5> CFD file: %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % % % SU2 configuration file % % Case description: Transonic inviscid optimization of a NACA0012 airfoil % % Author: Francisco Palacios % % Institution: Stanford University % % Date: 2013.09.29 % % File Version 5.0.0 "Raven" % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% % % Physical governing equations (EULER, NAVIER_STOKES, % WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY, % POISSON_EQUATION) SOLVER= EULER % % Mathematical problem (DIRECT, CONTINUOUS_ADJOINT) MATH_PROBLEM= DIRECT % % Restart solution (NO, YES) RESTART_SOL= YES % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% % % Mach number (non-dimensional, based on the free-stream values) MACH_NUMBER= 0.86 % % Angle of attack (degrees) AOA= 3.5 % % Free-stream pressure (101325.0 N/m^2 by default, only Euler flows) FREESTREAM_PRESSURE= 101325.0 % % Free-stream temperature (288.15 K by default) FREESTREAM_TEMPERATURE= 288.15 % ---------------------- 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 % % Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, % FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE % ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% % % Marker of the Euler boundary (0 = no marker) MARKER_EULER= ( airfoil ) % % Marker of the far field (0 = no marker) MARKER_FAR= ( farfield ) % ------------------------ SURFACES IDENTIFICATION ----------------------------% % % Marker of the surface which is going to be plotted or designed MARKER_PLOTTING= ( airfoil ) % % Marker of the surface where the functional (Cd, Cl, etc.) will be evaluated MARKER_MONITORING= ( airfoil ) % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% % % Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) NUM_METHOD_GRAD= GREEN_GAUSS % % Courant-Friedrichs-Lewy condition of the finest grid CFL_NUMBER= 10.0 % % 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 ) % % Number of total iterations ITER= 1000 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------% % % Linear solver for the implicit (or discrete adjoint) formulation (LU_SGS, % SYM_GAUSS_SEIDEL, BCGSTAB, GMRES) LINEAR_SOLVER= FGMRES % % Preconditioner of the Krylov linear solver (NONE, JACOBI, LINELET, LUSGS) LINEAR_SOLVER_PREC= LU_SGS % % Min error of the linear solver for the implicit formulation LINEAR_SOLVER_ERROR= 1E-4 % % Max number of iterations of the linear solver for the implicit formulation LINEAR_SOLVER_ITER= 2 % -------------------------- MULTIGRID PARAMETERS -----------------------------% % % Multi-Grid Levels (0 = no multi-grid) MGLEVEL= 2 % % Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE) MGCYCLE= V_CYCLE % % 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, ROE-1ST_ORDER, % ROE-2ND_ORDER) CONV_NUM_METHOD_FLOW= JST % % Slope limiter (VENKATAKRISHNAN) SLOPE_LIMITER_FLOW= VENKATAKRISHNAN % % 2nd and 4th order artificial dissipation coefficients JST_SENSOR_COEFF= ( 0.5, 0.02 ) % % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) TIME_DISCRE_FLOW= EULER_IMPLICIT % ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------% % Adjoint problem boundary condition (DRAG, LIFT, SIDEFORCE, MOMENT_X, % MOMENT_Y, MOMENT_Z, EFFICIENCY, % EQUIVALENT_AREA, NEARFIELD_PRESSURE, % FORCE_X, FORCE_Y, FORCE_Z, THRUST, % TORQUE) OBJECTIVE_FUNCTION= DRAG INCONSISTENT_DISC= NO % % Convective numerical method (JST, LAX-FRIEDRICH, ROE-1ST_ORDER, % ROE-2ND_ORDER) CONV_NUM_METHOD_ADJFLOW= JST % % Slope limiter (VENKATAKRISHNAN, SHARP_EDGES) SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN % % 2nd, and 4th order artificial dissipation coefficients ADJ_JST_SENSOR_COEFF= ( 0.0, 0.02 ) % % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT) TIME_DISCRE_ADJFLOW= EULER_IMPLICIT % % Reduction factor of the CFL coefficient in the adjoint problem CFL_REDUCTION_ADJFLOW= 0.8 % % Limit value for the adjoint variable LIMIT_ADJFLOW= 1E6 % ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------% % % Marker(s) of the surface where geometrical based function will be evaluated GEO_MARKER= ( airfoil ) % % Description of the geometry to be analyzed (AIRFOIL, WING, FUSELAGE) GEO_DESCRIPTION= AIRFOIL % % Geometrical evaluation mode (FUNCTION, GRADIENT) GEO_MODE= FUNCTION % ----------------------- DESIGN VARIABLE PARAMETERS --------------------------% % % Kind of deformation (FFD_SETTING, HICKS_HENNE, HICKS_HENNE_NORMAL, PARABOLIC, % HICKS_HENNE_SHOCK, NACA_4DIGITS, DISPLACEMENT, ROTATION, % FFD_CONTROL_POINT, FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE, % FFD_ROTATION) 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 % - HICKS_HENNE_FAMILY ( Lower(0)/Upper(1) side, x_Loc ) % - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit ) % - PARABOLIC ( 1st digit, 2nd and 3rd digit ) % - DISPLACEMENT ( x_Disp, y_Disp, z_Disp ) % - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) DV_PARAM= ( 1, 0.5 ) % % Value of the shape deformation deformation DV_VALUE= 1.0 % ------------------------ GRID DEFORMATION PARAMETERS ------------------------% % % Number of smoothing iterations for FEA mesh deformation DEFORM_LINEAR_SOLVER_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 % % Minimum residual criteria for the linear solver convergence of grid deformation DEFORM_LINEAR_SOLVER_ERROR= 1E-14 % % Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME, % WALL_DISTANCE, CONSTANT_STIFFNESS) DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME % --------------------------- CONVERGENCE PARAMETERS --------------------------% % % Min value of the residual (log10 of the residual) CONV_RESIDUAL_MINVAL= -13 % % Start Cauchy criteria at iteration number CONV_STARTITER= 10 % % Number of elements to apply the criteria CONV_CAUCHY_ELEMS= 100 % % Epsilon to control the series convergence CONV_CAUCHY_EPS= 1E-6 % ------------------------- 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_FILENAME= solution_flow.dat % % Restart adjoint input file SOLUTION_ADJ_FILENAME= solution_adj.dat % % Output tabular format (CSV, TECPLOT) 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 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_FILENAME= surface_flow % % Output file surface adjoint coefficient (w/o extension) SURFACE_ADJ_FILENAME= surface_adjoint % % % Screen output SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG) % % Output files OUTPUT_FILES = (RESTART, PARAVIEW, SURFACE_PARAVIEW, SURFACE_CSV) % --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------% % % Available flow based objective functions or constraint functions % DRAG, LIFT, SIDEFORCE, EFFICIENCY, BUFFET, % 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, % SURFACE_TOTAL_PRESSURE, SURFACE_MASSFLOW % SURFACE_STATIC_PRESSURE, SURFACE_MACH % % Available geometrical based objective functions or constraint functions % AIRFOIL_AREA, AIRFOIL_THICKNESS, AIRFOIL_CHORD, AIRFOIL_TOC, AIRFOIL_AOA, % WING_VOLUME, WING_MIN_THICKNESS, WING_MAX_THICKNESS, WING_MAX_CHORD, WING_MIN_TOC, WING_MAX_TWIST, WING_MAX_CURVATURE, WING_MAX_DIHEDRAL % STATION#_WIDTH, STATION#_AREA, STATION#_THICKNESS, STATION#_CHORD, STATION#_TOC, % STATION#_TWIST (where # is the index of the station defined in GEO_LOCATION_STATIONS) % % Available design variables % 2D Design variables % FFD_CONTROL_POINT_2D ( 19, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, x_Mov, y_Mov ) % FFD_CAMBER_2D ( 20, Scale | Mark. List | FFD_BoxTag, i_Ind ) % FFD_THICKNESS_2D ( 21, Scale | Mark. List | FFD_BoxTag, i_Ind ) % FFD_TWIST_2D ( 22, Scale | Mark. List | FFD_BoxTag, x_Orig, y_Orig ) % HICKS_HENNE ( 30, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc ) % ANGLE_OF_ATTACK ( 101, Scale | Mark. List | 1.0 ) % % 3D Design variables % FFD_CONTROL_POINT ( 11, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov ) % FFD_NACELLE ( 12, Scale | Mark. List | FFD_BoxTag, rho_Ind, theta_Ind, phi_Ind, rho_Mov, phi_Mov ) % FFD_GULL ( 13, Scale | Mark. List | FFD_BoxTag, j_Ind ) % FFD_CAMBER ( 14, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind ) % FFD_TWIST ( 15, Scale | Mark. List | FFD_BoxTag, j_Ind, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) % FFD_THICKNESS ( 16, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind ) % FFD_ROTATION ( 18, Scale | Mark. List | FFD_BoxTag, x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) % FFD_ANGLE_OF_ATTACK ( 24, Scale | Mark. List | FFD_BoxTag, 1.0 ) % % Global design variables % TRANSLATION ( 1, Scale | Mark. List | x_Disp, y_Disp, z_Disp ) % ROTATION ( 2, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) % % Optimization objective function with scaling factor, separated by semicolons. % To include quadratic penalty function: use OPT_CONSTRAINT option syntax within the OPT_OBJECTIVE list. % ex= Objective * Scale OPT_OBJECTIVE= DRAG % % Optimization constraint functions with pushing factors (affects its value, not the gradient % in the python scripts), separated by semicolons % ex= (Objective = Value ) * Scale, use '>','<','=' OPT_CONSTRAINT= NONE % % Factor to reduce the norm of the gradient (affects the objective function and gradient in the python scripts) % In general, a norm of the gradient ~1E-6 is desired. OPT_GRADIENT_FACTOR= 1E-6 % % Factor to relax or accelerate the optimizer convergence (affects the line search in SU2_DEF) % In general, surface deformations of 0.01'' or 0.0001m are desirable OPT_RELAX_FACTOR= 1E3 % % Maximum number of optimizer iterations OPT_ITERATIONS= 100 % % Requested accuracy OPT_ACCURACY= 1E-10 % % Upper bound for each design variable OPT_BOUND_UPPER= 0.1 % % Lower bound for each design variable OPT_BOUND_LOWER= -0.1 % % Optimization design variables, separated by semicolons 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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