[bornax]

I'm running an optimization at a certain Mach number and AoA on a self defined airfoil. I've created the mesh in gmsh with two different markers for the upper and lower side of the airfoil. (I've allready done several successful simulations with SU2_CFD with this airfoil)
At the moment i've no constraints and i minimize DRAG. I launch shape_optimization.py with "-g CONTINUOUS_ADJOINT -o SLSQP" and the options for parallel computing.
The optimization reaches the convergence but i've realized that only the points of the upper side are modified. I've checked this looking in "DESIGNS/DSN_.../DEFORM/config_DEF.cfg" where i see something like this:

%-----------------------------------------------------------------------------%
GEO_MARKER= ( airfoil_up, airfoil_lo )
GEO_DESCRIPTION= AIRFOIL
GEO_MODE= FUNCTION
DV_KIND= HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE, HICKS_HENNE
DV_MARKER= ( airfoil_up )
DV_PARAM= ( 1.0, 0.05) ; ( 1.0, 0.1) ; ( 1.0, 0.15) ; ( 1.0, 0.2) ; ( 1.0, 0.25) ; ( 1.0, 0.3) ; ( 1.0, 0.35) ; ( 1.0, 0.4) ; ( 1.0, 0.45) ; ( 1.0, 0.5) ; ( 1.0, 0.55) ; ( 1.0, 0.6) ; ( 1.0, 0.65) ; ( 1.0, 0.7) ; ( 1.0, 0.75) ; ( 1.0, 0.8) ; ( 1.0, 0.85) ; ( 1.0, 0.9) ; ( 1.0, 0.95) ; ( 0.0, 0.05) ; ( 0.0, 0.1) ; ( 0.0, 0.15) ; ( 0.0, 0.2) ; ( 0.0, 0.25) ; ( 0.0, 0.3) ; ( 0.0, 0.35) ; ( 0.0, 0.4) ; ( 0.0, 0.45) ; ( 0.0, 0.5) ; ( 0.0, 0.55) ; ( 0.0, 0.6) ; ( 0.0, 0.65) ; ( 0.0, 0.7) ; ( 0.0, 0.75) ; ( 0.0, 0.8) ; ( 0.0, 0.85) ; ( 0.0, 0.9) ; ( 0.0, 0.95)
DV_VALUE= -2.3933e-07, -2.40235e-07, -2.08344e-07, -1.63663e-07, -1.15148e-07, -6.81409e-08, -2.62537e-08, 8.10047e-09, 3.36207e-08, 5.01587e-08, 5.86974e-08, 6.11612e-08, 6.00312e-08, 5.78369e-08, 5.66847e-08, 5.80158e-08, 6.28639e-08, 7.35168e-08, 1.0271e-07, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0

...
...
...

DEFINITION_DV= ( 1 , 1.0 | airfoil_up | 1.0 , 0.05 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.1 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.15 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.2 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.25 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.3 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.35 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.4 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.45 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.5 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.55 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.6 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.65 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.7 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.75 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.8 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.85 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.9 ); ( 1 , 1.0 | airfoil_up | 1.0 , 0.95 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.05 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.1 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.15 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.2 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.25 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.3 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.35 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.4 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.45 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.5 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.55 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.6 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.65 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.7 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.75 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.8 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.85 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.9 ); ( 1 , 1.0 | airfoil_lo | 0.0 , 0.95 )
DV_VALUE_NEW= -2.3933e-07, -2.40235e-07, -2.08344e-07, -1.63663e-07, -1.15148e-07, -6.81409e-08, -2.62537e-08, 8.10047e-09, 3.36207e-08, 5.01587e-08, 5.86974e-08, 6.11612e-08, 6.00312e-08, 5.78369e-08, 5.66847e-08, 5.80158e-08, 6.28639e-08, 7.35168e-08, 1.0271e-07, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0
DV_VALUE_OLD= 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0
%----------------------------------------------------------------------------%

So, even if the code recognizes 38 design variables, it perturbates only the first 19 variables that correspond to the upper side (which i have defined with the tag "airfoil_up").

I think that i make some mistakes in the .cfg file related to "airfoil_up" and "airfoil_lo" which, for me, are the markers of upper and lower side respectively.

I tryed to look for a similar definition of the airfoil in this forum, but i couldn't find anything.
I've only found at this thread:
Using multiple Hicks Henne deformations
something that maybe could be useful for me, but trying for example with:
%--------------------------------------------------%
DV_KIND=HICKS_HENNE, HICKS_HENNE
DV_PARAM = (1.0, 0.5); (0.0, 0.5)
%--------------------------------------------------%
didn't make any difference.

In my .cfg file i have:

%-----------------------------------------------------------------------%
% ----------------------- 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_up, airfoil_lo )
%
% 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

% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
OPT_OBJECTIVE= DRAG
OPT_CONSTRAINT= NONE
OPT_GRADIENT_FACTOR= 1E-6
OPT_RELAX_FACTOR= 1E2
OPT_ITERATIONS= 100
%
% Requested accuracy
OPT_ACCURACY= 1E-9
%
% Upper bound for each design variable
OPT_BOUND_UPPER= 0.1
% Lower bound for each design variable
OPT_BOUND_LOWER= -0.1

DEFINITION_DV= ( 1, 1.0 | airfoil_up | 1, 0.05 ); ( 1, 1.0 | airfoil_up | 1, 0.10 ); ( 1, 1.0 | airfoil_up | 1, 0.15 ); ( 1, 1.0 | airfoil_up | 1, 0.20 ); ( 1, 1.0 | airfoil_up | 1, 0.25 ); ( 1, 1.0 | airfoil_up | 1, 0.30 ); ( 1, 1.0 | airfoil_up | 1, 0.35 ); ( 1, 1.0 | airfoil_up | 1, 0.40 ); ( 1, 1.0 | airfoil_up | 1, 0.45 ); ( 1, 1.0 | airfoil_up | 1, 0.50 ); ( 1, 1.0 | airfoil_up | 1, 0.55 ); ( 1, 1.0 | airfoil_up | 1, 0.60 ); ( 1, 1.0 | airfoil_up | 1, 0.65 ); ( 1, 1.0 | airfoil_up | 1, 0.70 ); ( 1, 1.0 | airfoil_up | 1, 0.75 ); ( 1, 1.0 | airfoil_up | 1, 0.80 ); ( 1, 1.0 | airfoil_up | 1, 0.85 ); ( 1, 1.0 | airfoil_up | 1, 0.90 ); ( 1, 1.0 | airfoil_up | 1, 0.95 );( 1, 1.0 | airfoil_lo | 0, 0.05 ); ( 1, 1.0 | airfoil_lo | 0, 0.10 ); ( 1, 1.0 | airfoil_lo | 0, 0.15 ); ( 1, 1.0 | airfoil_lo | 0, 0.20 ); ( 1, 1.0 | airfoil_lo | 0, 0.25 ); ( 1, 1.0 | airfoil_lo | 0, 0.30 ); ( 1, 1.0 | airfoil_lo | 0, 0.35 ); ( 1, 1.0 | airfoil_lo | 0, 0.40 ); ( 1, 1.0 | airfoil_lo | 0, 0.45 ); ( 1, 1.0 | airfoil_lo | 0, 0.50 ); ( 1, 1.0 | airfoil_lo | 0, 0.55 ); ( 1, 1.0 | airfoil_lo | 0, 0.60 ); ( 1, 1.0 | airfoil_lo | 0, 0.65 ); ( 1, 1.0 | airfoil_lo | 0, 0.70 ); ( 1, 1.0 | airfoil_lo | 0, 0.75 ); ( 1, 1.0 | airfoil_lo | 0, 0.80 ); ( 1, 1.0 | airfoil_lo | 0, 0.85 ); ( 1, 1.0 | airfoil_lo | 0, 0.90 ); ( 1, 1.0 | airfoil_lo | 0, 0.95 )

%----------------------------------------------------------------------------%

I'm not sure about my definition of DV_PARAM and DEFINITION_DV.

I know that a solution could be to define a mesh with only one MARKER of the airfoil and put the design variables in the right order but i would like to maintain two separate markers for the upper and lower side.

I hope to have posted in the right way, this is my first post!

[tomp1993]

Hi,
I have also had this issue when using Hicks-Henne bumps - only one surface being designed at a time!
try using:
DV_PARAM= ( 0, X_loc); (1, X_loc)
I can't remember if it worked perfectly like this but definitely worth a go.
Best Wishes
Tom

[bornax]

Hi Tom,
thanks for your answer!
Unfortunately i've allready tried your solution but it doesn't work.
Even if i've defined in the .cfg file two markers:

DV_MARKER= ( airfoil_up, airfoil_lo )

and:

DV_PARAM = (1.0, 0.5); (0.0, 0.5)

Then in the "DESIGNS/DSN_002/DEFORM/config_DEF.cfg" file only one marker is reported:

DV_MARKER= ( airfoil_up )

[Umuteng]

Thank you for the question, I am faced with very similar problem. Did you find a solution?

[wallym]

Hi Umuteng (and all),

While using the SU2_DEF file is not my strength, you can set the Hicks-Henne Bunmp design variables for an airfoil/2d-shape as follows:

DEFINITION_DV= ( 30, 1.0 | airfoil | 1, 0.05 );

The numbers would be be as follows:
30 -> This specifies Hicks-Henne.
1.0 -> Scaling factor that is normally set at 1.
airfoil -> This is marker for the entire surface of body in question
1 -> This specifies the top (1) or bottom (0) of the body (specified above) airfoil
0.05 -> the x location of the bump function.

There are several tutorials at https://su2code.github.io/tutorials/ in the 'Design Features' pull down.

My understanding of the Hicks-Henne bumps is that it needs to be a singular surface.

You can try to replace to the "|airfoil|" portion of the above the code to something like "|airfoil_up, airfoil_down|". If the doesnt work, you can definitely used 2D FFD boxes.

Let me know that goes,
Wally