[topheruk29]

Can anyone advise on how to implement additional shape parameterisation methods within SU2 e.g. PARSEC. There is not much info available, despite similar posts on which.



My current understanding:

tools.py - the dv_map has a dictionary option for "CUSTOM" design variable

grid_movement_structure.cpp - each method has a subroutine that SU2_DOT calls e.g. SetCST(geometry, config, iDV, true);


Do I just need to add a subroutine to the file grid_movement_structure.cpp, named "CUSTOM" e.g. SetCUSTOM(geometry, config, iDV, true)?


*UPDATE*
After a bit more reading, I think the solution is to use DV_KIND=SURFACE_FILE and use the coordinates generated outside of SU2 using the design variables specific to other methods



Thanks in advance.

[tomp1993]

hi,
could you please provide a little more info on how you used the SURFACE_FILE option for optimization?
and is it effective? does SU2 interpolate between the initial surface grid and the new one provided by SURFACE_FILE?
thanks
Tom

[topheruk29]

Hi tom,


I run the optimisation separate from SU2 and then write the aerofoil coordinates in a file that SU2_DEF reads to update an existing mesh.


To do this, I first ran SU2_DEF with the config file* (def_NACA0012.cfg) in SU2/TestCases/deformation/naca0012 and with a mesh in the same folder (e.g. mesh_NACA0012_inv.SU2).



This created a file called mesh_motion.dat that provides the format for your own aerofoil coordinates. Replace this file and run SU2_DEF again but with the mesh_out.SU2 file that is created and the original mesh is updated. Make sure that you have the same number of aerofoil coordinates as the original number of data points.


*I made the following changes to the config file:
DV_KIND= SURFACE_FILE

DV_MARKER= ( airfoil )
DV_PARAM= ( 1, 0.5 )
DV_VALUE= 0.1
% Surface deformation input filename (SURFACE_FILE DV only)
MOTION_FILENAME= mesh_motion.dat
GRID_MOVEMENT= YES
GRID_MOVEMENT_KIND= EXTERNAL
MARKER_MOVING=( airfoil )


Not sure how effective this method is, I am still implementing it within my optimisation code. I only tested the deformations with the same aerfoil design but with a blunt trailing edge instead. There was a highly skewed cell at the trailing edge that I think is probably because the original mesh was not created for the blunt trailing edge.



Hope this helps.



Chris