[YoniHe]

Hi everyone,


I am learning how to make an optimization on an airfoil, with Hicks-Henne geometric variables. I want to add AOA to be a design variable. So the design variables including Hicks-Henne airfoil variables and AOA. The optimization problem is derived slightly from tutorial 7 "Optimal Shape Design of a Rotating Airfoil", which is a common example in aircraft design:
Minimize: drag coefficent at Ma = 0.75
subject to: CL=0.3, Max_THICKNESS > 0.12
design variables: Hicks-Henne parameters and AOA


I have added AOA to the end of "DEFINITION_DV" in .cfg file. The same mesh file was used as tutorial 7. When I carried out the process, something was wrong. Can someone help me? (I am using version 3.2.2) Thanks!

error displayed:
New Design: DESIGNS/DSN_001
./DESIGNS/DSN_001
Evalaute Equality Constraints
Lift... DV_KIND: invalid option value HICKS_HENNE
DV_PARAM: may not have ending semicolon

DV_KIND: invalid option value HICKS_HENNE
DV_PARAM: may not have ending semicolon
DV_KIND: invalid option value HICKS_HENNE
DV_PARAM: may not have ending semicolon

DV_KIND: invalid option value HICKS_HENNE
DV_PARAM: may not have ending semicolon


-------------------------------------------------------
Primary job terminated normally, but 1 process returned
a non-zero exit code.. Per user-direction, the job has been aborted.
-------------------------------------------------------
--------------------------------------------------------------------------
mpirun detected that one or more processes exited with non-zero status, thus causing
the job to be terminated. The first process to do so was:

Process name: [[49933,1],1]
Exit code: 1
--------------------------------------------------------------------------
Traceback (most recent call last):
File "/data/hedaquanhe/SU2/bin/shape_optimization.py", line 130, in <module>
main()
File "/data/hedaquanhe/SU2/bin/shape_optimization.py", line 75, in main
options.step ) #finite difference step default=1e-4
File "/data/hedaquanhe/SU2/bin/shape_optimization.py", line 113, in shape_optimization
SU2.opt.SLSQP(project,x0,xb,its) # 'SU2.opt.__init__.py' from scipy_tools import scipy_slsqp as SLSQP(it is a function)
File "/data/hedaquanhe/SU2/bin/SU2/opt/scipy_tools.py", line 102, in scipy_slsqp
epsilon = 1.0e-06 )#control command
File "/opt/apps/python-2.7/lib/python2.7/site-packages/scipy/optimize/slsqp.py", line 199, in fmin_slsqp
constraints=cons, **opts)
File "/opt/apps/python-2.7/lib/python2.7/site-packages/scipy/optimize/slsqp.py", line 300, in _minimize_slsqp
meq = sum(map(len, [atleast_1d(c['fun'](x, *c['args'])) for c in cons['eq']]))
File "/data/hedaquanhe/SU2/bin/SU2/opt/scipy_tools.py", line 152, in con_ceq
cons = project.con_ceq(x)
File "/data/hedaquanhe/SU2/bin/SU2/opt/project.py", line 213, in con_ceq
return self._eval(konfig, func,dvs)
File "/data/hedaquanhe/SU2/bin/SU2/opt/project.py", line 172, in _eval
vals = design._eval(func,*args)
File "/data/hedaquanhe/SU2/bin/SU2/eval/design.py", line 132, in _eval
vals = eval_func(*inputs)
File "/data/hedaquanhe/SU2/bin/SU2/eval/design.py", line 325, in con_ceq
func = su2func(this_con,config,state)
File "/data/hedaquanhe/SU2/bin/SU2/eval/functions.py", line 75, in function
aerodynamics( config, state )
File "/data/hedaquanhe/SU2/bin/SU2/eval/functions.py", line 152, in aerodynamics
info = update_mesh(config,state)
File "/data/hedaquanhe/SU2/bin/SU2/eval/functions.py", line 541, in update_mesh
info = su2run.decompose(config)
File "/data/hedaquanhe/SU2/bin/SU2/run/decompose.py", line 66, in decompose
SU2_PRT(konfig)
File "/data/hedaquanhe/SU2/bin/SU2/run/interface.py", line 73, in PRT
run_command( the_Command )
File "/data/hedaquanhe/SU2/bin/SU2/run/interface.py", line 277, in run_command
raise Exception , message
Exception: Path = /home/hedaquanhe/test2/DESIGNS/DSN_001/DECOMP/,
Command = mpirun -n 4 /data/hedaquanhe/SU2/bin/SU2_PRT config_PRT.cfg
SU2 process returned error '1'

My .cfg file is:

% ------------- 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, LINEARIZED, ONE_SHOT_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= 0.75
%
% Angle of attack (degrees)
%AoA= 0
%
% Side-slip angle (degrees)
SIDESLIP_ANGLE= 0.0
%
% 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_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

% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
%
% Dynamic mesh simulation (NO, YES)
%%GRID_MOVEMENT= YES
%
% Type of dynamic mesh (NONE, RIGID_MOTION, DEFORMING, ROTATING_FRAME,
% MOVING_WALL, FLUID_STRUCTURE, AEROELASTIC, EXTERNAL)
%%GRID_MOVEMENT_KIND= ROTATING_FRAME
%
% Motion mach number (non-dimensional). Used for intitializing a viscous flow
% with the Reynolds number and for computing force coeffs. with dynamic meshes.
%%MACH_MOTION= 0.79578199852934983
%
% Coordinates of the motion origin
%%MOTION_ORIGIN_X= 0.5
%%MOTION_ORIGIN_Y= -32.0
%%MOTION_ORIGIN_Z= 0.0
%
% Angular velocity vector (rad/s) about the motion origin
%%ROTATION_RATE_X = 0.0
%%ROTATION_RATE_Y = 0.0
%%ROTATION_RATE_Z = 8.25

% ----------------------- 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 )
%
% 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 TO DEFINE THE NUMERICAL METHOD --------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
% Courant-Friedrichs-Lewy condition of the finest grid
CFL_NUMBER= 6.0
%
% CFL ramp (factor, number of iterations, CFL limit)
CFL_RAMP= ( 1.0, 100, 0.1 )
%
% Runge-Kutta alpha coefficients
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
%
% Number of total iterations
EXT_ITER= 300

% ------------------------ 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
%
% Maximum number of children in the agglomeration stage
MAX_CHILDREN= 250
%
% Maximum length of an agglomerated element (compared with the domain)
MAX_DIMENSION= 0.2
%
% 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= 0.95
%
% Damping factor for the correction prolongation
MG_DAMP_PROLONGATION= 0.95
%
% Full Multigrid (NO, YES)
FULLMG= NO
%
% Start up iterations using the fine grid
START_UP_ITER= 0

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, ROE, AUSM, HLLC)
CONV_NUM_METHOD_FLOW= JST
%
% Slope limiter (VENKATAKRISHNAN)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% Coefficient for the limiter
LIMITER_COEFF= 0.3
%
% 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 -------------------%
%
% 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)
CONV_NUM_METHOD_ADJFLOW= JST
%
% Slope limiter (VENKATAKRISHNAN, SHARP_EDGES)
SLOPE_LIMITER_ADJFLOW= SHARP_EDGES
%
% Coefficient for the sharp edges limiter
SHARP_EDGES_COEFF= 3.0
%
% 1st, 2nd, and 4th order artificial dissipation coefficients
AD_COEFF_ADJFLOW= ( 0.15, 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
%
% Remove sharp edges from the sensitivity evaluation (NO, YES)
SENS_REMOVE_SHARP= NO
%
% Sensitivity smoothing (NONE, SOBOLEV, BIGRID)
SENS_SMOOTHING= NONE
%
% Adjoint frozen viscosity (NO, YES)
FROZEN_VISC= YES

% --------------------------- PARTITIONING STRATEGY ---------------------------%
%
% Write a paraview file for each partition (NO, YES)
VISUALIZE_PART= NO

% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------%
%
% Geometrical evaluation mode (FUNCTION, GRADIENT)
GEO_MODE= FUNCTION
%
% Marker(s) of the surface where geometrical based func. will be evaluated
GEO_MARKER= ( airfoil )

% ------------------------ GRID DEFORMATION 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 )
%
% Old value of the deformation for incremental deformations
DV_VALUE= 0.05
%
% Visualize the deformation (NO, YES)
VISUALIZE_DEFORMATION= NO

% --------------------------- CONVERGENCE PARAMETERS --------------------------%
% Convergence criteria (CAUCHY, RESIDUAL)
%
CONV_CRITERIA= RESIDUAL
%
% Residual reduction (order of magnitude with respect to the initial value)
RESIDUAL_REDUCTION= 8
%
% Min value of the residual (log10 of the residual)
RESIDUAL_MINVAL= -13
%
% 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
CAUCHY_FUNC_ADJFLOW= SENS_MACH
%
% Epsilon for full multigrid method evaluation
FULLMG_CAUCHY_EPS= 1E-3

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
% Mesh input file
MESH_FILENAME= mesh_NACA0012_rot.su2
%
% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
MESH_FORMAT= SU2
%
% Convert a CGNS mesh to SU2 format (YES, NO)
CGNS_TO_SU2= NO
%
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 (PARAVIEW, TECPLOT, STL)
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 linear flow
RESTART_LIN_FILENAME= restart_lin.dat
%
% Output file flow (w/o extension) variables
VOLUME_FLOW_FILENAME= flow
%
% Output file adjoint (w/o extension) variables
VOLUME_ADJ_FILENAME= adjoint
%
% Output file linearized (w/o extension) variables
VOLUME_LIN_FILENAME= linearized
%
% 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
%
% Output file surface linear coefficient (w/o extension)
SURFACE_LIN_FILENAME= surface_linear
%
% Writing solution file frequency
WRT_SOL_FREQ= 250
%
% Writing convergence history frequency
WRT_CON_FREQ= 1

% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
% Available Objective functions
% DRAG, LIFT, SIDEFORCE, PRESSURE, FORCE_X, FORCE_Y,
% FORCE_Z, MOMENT_X, MOMENT_Y, MOMENT_Z, EFFICIENCY,
% EQUIVALENT_AREA, THRUST, TORQUE, FREE_SURFACE

% Optimization objective function with optional 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 = 0.3)*0.001; ( MAX_THICKNESS > 0.12 ) * 0.001
%
% List of design variables (Design variables are separated by semicolons)
% From 1 to 99, Geometrycal design variables.
% - HICKS_HENNE ( 1, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc )
% - NACA_4DIGITS ( 4, Scale | Mark. List | 1st digit, 2nd digit, 3rd and 4th digit )
% - ROTATION ( 6, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn )
% From 100 to 199, Flow solver design variables.
% - MACH_NUMBER ( 101, Scale | Markers List )
% - AOA ( 102, Scale | Markers List )
DEFINITION_DV= ( 1, 1.0 | airfoil | 0, 0.961538461538 ); ( 1, 1.0 | airfoil | 0, 0.923076923077 ); ( 1, 1.0 | airfoil | 0, 0.884615384615 ); ( 1, 1.0 | airfoil | 0, 0.846153846154 ); ( 1, 1.0 | airfoil | 0, 0.807692307692 ); ( 1, 1.0 | airfoil | 0, 0.769230769231 ); ( 1, 1.0 | airfoil | 0, 0.730769230769 ); ( 1, 1.0 | airfoil | 0, 0.692307692308 ); ( 1, 1.0 | airfoil | 0, 0.653846153846 ); ( 1, 1.0 | airfoil | 0, 0.615384615385 ); ( 1, 1.0 | airfoil | 0, 0.576923076923 ); ( 1, 1.0 | airfoil | 0, 0.538461538462 ); ( 1, 1.0 | airfoil | 0, 0.5 ); ( 1, 1.0 | airfoil | 0, 0.461538461538 ); ( 1, 1.0 | airfoil | 0, 0.423076923077 ); ( 1, 1.0 | airfoil | 0, 0.384615384615 ); ( 1, 1.0 | airfoil | 0, 0.346153846154 ); ( 1, 1.0 | airfoil | 0, 0.307692307692 ); ( 1, 1.0 | airfoil | 0, 0.269230769231 ); ( 1, 1.0 | airfoil | 0, 0.230769230769 ); ( 1, 1.0 | airfoil | 0, 0.192307692308 ); ( 1, 1.0 | airfoil | 0, 0.153846153846 ); ( 1, 1.0 | airfoil | 0, 0.115384615385 ); ( 1, 1.0 | airfoil | 0, 0.0769230769231 ); ( 1, 1.0 | airfoil | 0, 0.0384615384615 ); ( 1, 1.0 | airfoil | 1, 0.0384615384615 ); ( 1, 1.0 | airfoil | 1, 0.0769230769231 ); ( 1, 1.0 | airfoil | 1, 0.115384615385 ); ( 1, 1.0 | airfoil | 1, 0.153846153846 ); ( 1, 1.0 | airfoil | 1, 0.192307692308 ); ( 1, 1.0 | airfoil | 1, 0.230769230769 ); ( 1, 1.0 | airfoil | 1, 0.269230769231 ); ( 1, 1.0 | airfoil | 1, 0.307692307692 ); ( 1, 1.0 | airfoil | 1, 0.346153846154 ); ( 1, 1.0 | airfoil | 1, 0.384615384615 ); ( 1, 1.0 | airfoil | 1, 0.423076923077 ); ( 1, 1.0 | airfoil | 1, 0.461538461538 ); ( 1, 1.0 | airfoil | 1, 0.5 ); ( 1, 1.0 | airfoil | 1, 0.538461538462 ); ( 1, 1.0 | airfoil | 1, 0.576923076923 ); ( 1, 1.0 | airfoil | 1, 0.615384615385 ); ( 1, 1.0 | airfoil | 1, 0.653846153846 ); ( 1, 1.0 | airfoil | 1, 0.692307692308 ); ( 1, 1.0 | airfoil | 1, 0.730769230769 ); ( 1, 1.0 | airfoil | 1, 0.769230769231 ); ( 1, 1.0 | airfoil | 1, 0.807692307692 ); ( 1, 1.0 | airfoil | 1, 0.846153846154 ); ( 1, 1.0 | airfoil | 1, 0.884615384615 ); ( 1, 1.0 | airfoil | 1, 0.923076923077 ); ( 1, 1.0 | airfoil | 1, 0.961538461538 ); ( 102, 1.0 | airfoil )

[DarioC]

Hello to everyone, I am new in this forum.
I can't even run the tutorial because I always get the same error, like YoniHe. ("SU2 process returned error '1').
I tried for three weeks and I am still in trouble! Does anyone know which is the solution, please?
(The problem occurs only when trying to run a python script, the direct calculation works fine!)

Dario

[YoniHe]

Can anyone help me with this problem?

[HwaYoung]

Hello,
I am a novice user of CFD as well as SU2.

I installed the SU2v4.1.0-64 bit for Windows 7, Python 2.7.10-64 bit, scipy 0.16.1, and numpy 1.9.2.

I set the environment variables as each variable name of "SU2_RUN" and "SU2_HOME" with the same variable value "C:\SU2" which containing SU2_XXX.exe, SU2_XXX source code files and SU2_PY.

I could run the Quick Start tutorial successfully but still have a problem in the tutorial "Optimal Shape Design of a Transonic Airfoil" as the same problem like others.. (SU2 process returned error '1')

I followed the tutorial but the 'history_project.dat' as a result file was like the attached file with just one evaluation number..
And there was a message in the log_Ajoint file created in C:\SU2\DESIGNS\DSN_001\ADJOINT_DRAG directory after 'Exit Success' message.
------------------------- Exit Success (SU2_CFD) ------------------------

MATH_PROBLEM: improper option value for type math problem
OPT_BOUND_UPPER: invalid option name. Check current SU2 options in config_template.cfg.
OPT_BOUND_LOWER: invalid option name. Check current SU2 options in config_template.cfg.


Please help me to run and finish this tutorial.

Thank you!