Unable to preform multipoint optimization with geometry constraints

[qooin1025]

I've been using su2's single point optimization for a while.
Now, I want to process a multipoint optimization with constraints.
The problem I encountered is that, if I set OPT_CONSTRAINT=NONE or a flow based constraint function(e.g. MULTIPOINT_MOMENT_Z), the optimization goes well.
But if the geometry based constraint is given to OPT_CONSTRAINT(e.g. OPT_CONSTRAINT=( AIRFOIL_THICKNESS>0)*0.001 like single point problem ), the error will occur as below.
The cfg file is based on inv_NACA0012_multipoint.cfg that is from TestCase.
I have no idea what the problem is. I can't find the answer anywhere else.
The error message is as follows:

Traceback (most recent call last):
File "/home/star/su2/bin/shape_optimization.py", line 183, in
main()
File "/home/star/su2/bin/shape_optimization.py", line 92, in main
shape_optimization( options.filename ,
File "/home/star/su2/bin/shape_optimization.py", line 159, in shape_optimization
SU2.opt.SLSQP(project,x0,xb,its,accu)
File "/home/star/su2/bin/SU2/opt/scipy_tools.py", line 120, in scipy_slsqp
outputs = fmin_slsqp( x0 = x0 ,
File "/usr/local/python/lib/python3.8/site-packages/scipy/optimize/_slsqp_py.py", line 206, in fmin_slsqp
res = _minimize_slsqp(func, x0, args, jac=fprime, bounds=bounds,
File "/usr/local/python/lib/python3.8/site-packages/scipy/optimize/_slsqp_py.py", line 374, in _minimize_slsqp
sf = _prepare_scalar_function(func, x, jac=jac, args=args, epsilon=eps,
File "/usr/local/python/lib/python3.8/site-packages/scipy/optimize/_optimize.py", line 263, in _prepare_scalar_function
sf = ScalarFunction(fun, x0, args, grad, hess,
File "/usr/local/python/lib/python3.8/site-packages/scipy/optimize/_differentiable_functions.py", line 158, in init
self._update_fun()
File "/usr/local/python/lib/python3.8/site-packages/scipy/optimize/_differentiable_functions.py", line 251, in _update_fun
self._update_fun_impl()
File "/usr/local/python/lib/python3.8/site-packages/scipy/optimize/_differentiable_functions.py", line 155, in update_fun
self.f = fun_wrapped(self.x)
File "/usr/local/python/lib/python3.8/site-packages/scipy/optimize/_differentiable_functions.py", line 137, in fun_wrapped
fx = fun(np.copy(x), *args)
File "/home/star/su2/bin/SU2/opt/scipy_tools.py", line 383, in obj_f
obj_list = project.obj_f(x)
File "/home/star/su2/bin/SU2/opt/project.py", line 237, in obj_f
return self._eval(konfig, func,dvs)
File "/home/star/su2/bin/SU2/opt/project.py", line 206, in _eval
vals = design._eval(func,*args)
File "/home/star/su2/bin/SU2/eval/design.py", line 147, in _eval
vals = eval_func(*inputs)
File "/home/star/su2/bin/SU2/eval/design.py", line 244, in obj_f
func += su2func(this_obj,config,state) * sign * scale * global_factor
File "/home/star/su2/bin/SU2/eval/functions.py", line 100, in function
multipoint( config, state )
File "/home/star/su2/bin/SU2/eval/functions.py", line 675, in multipoint
func[i+1] = aerodynamics(konfig,ztate)
File "/home/star/su2/bin/SU2/eval/functions.py", line 313, in aerodynamics
funcs[key] = state['FUNCTIONS'][key]
KeyError: 'AIRFOIL_AREA

The cfg file is as follows:

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Transonic inviscid optimization of a NACA0012 airfoil %
% Author: Indiana Stokes %
% Institution: %
% Date: 2017.07.03 %
% File Version 7.3.1 "Blackbird" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%
% ------------- 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= 0.8
%
% 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 (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= 5.0
%
% 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= 100
%
% ------------------------ 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= 0
%
% 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
%
% 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, FREE_SURFACE)
OBJECTIVE_FUNCTION= DRAG
%
% Convective numerical method (JST, LAX-FRIEDRICH, ROE-1ST_ORDER,
% ROE-2ND_ORDER)
CONV_NUM_METHOD_ADJFLOW= JST
%
% 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
%
% ----------------------- 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
%
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
%
% Writing solution file frequency
OUTPUT_WRT_FREQ= 250
%
%
% --------------------- 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 )
%
% Definition of multipoint design problems, this option should be combined with the
% the prefix MULTIPOINT in the objective function or constraint (e.g. MULTIPOINT_DRAG, MULTIPOINT_LIFT, etc.)
MULTIPOINT_WEIGHT= (0.25, 0.5, 0.25)
MULTIPOINT_MACH_NUMBER= (0.79, 0.8, 0.81)
%MULTIPOINT_AOA= (1.25, 1.25, 1.25)
%MULTIPOINT_SIDESLIP_ANGLE= (0.0, 0.0, 0.0)
%MULTIPOINT_REYNOLDS_NUMBER= (1E6, 1E6, 1E6)
%MULTIPOINT_TARGET_CL= (0.8, 0.8, 0.8)
%MULTIPOINT_FREESTREAM_PRESSURE= (101325.0, 101325.0, 101325.0)
%MULTIPOINT_FREESTREAM_TEMPERATURE= (288.15, 288.15, 288.15)
%
% Optimization objective function with scaling factor
% ex= Objective * Scale
OPT_OBJECTIVE= MULTIPOINT_DRAG * 0.001
%
% Optimization constraint functions with scaling factors, separated by semicolons
% ex= (Objective = Value ) * Scale, use '>','<','='
%
%OPT_CONSTRAINT=NONE
%everything is well
%
%OPT_OBJECTIVE=(MULTIPOINT MOMENT_Z>0)*0.001
%everything is well
%
OPT_CONSTRAINT= (AIRFOIL_THICKNESS>0)*0.001
%Error will occur%
%
% Maximum number of optimizer iterations
OPT_ITERATIONS= 100
%
% Requested accuracy
OPT_ACCURACY= 1E-6
%
% Upper bound for each design variable
OPT_BOUND_UPPER= 1E6
%
% Lower bound for each design variable
OPT_BOUND_LOWER= -1E6
%
% 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 )

[EngJamal2023]

have your problem has been fixed ,i hope to share with me your result