CFD Online Logo CFD Online URL
Home > Forums > Software User Forums > SU2 > SU2 Shape Design

Custom Shape Parameterisation Methods

Register Blogs Members List Search Today's Posts Mark Forums Read

LinkBack Thread Tools Search this Thread Display Modes
Old   June 5, 2018, 09:11
Default Custom Shape Parameterisation Methods
New Member
Join Date: Mar 2018
Posts: 5
Rep Power: 8
topheruk29 is on a distinguished road
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: - 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)?

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.

Last edited by topheruk29; June 5, 2018 at 10:18.
topheruk29 is offline   Reply With Quote

Old   June 7, 2018, 10:27
tom pratt
Join Date: Jan 2016
Posts: 55
Rep Power: 10
tomp1993 is on a distinguished road
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?
tomp1993 is offline   Reply With Quote

Old   June 8, 2018, 13:46
New Member
Join Date: Mar 2018
Posts: 5
Rep Power: 8
topheruk29 is on a distinguished road
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_MARKER= ( airfoil )
DV_PARAM= ( 1, 0.5 )
% Surface deformation input filename (SURFACE_FILE DV only)
MOTION_FILENAME= mesh_motion.dat
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.

topheruk29 is offline   Reply With Quote

Old   January 19, 2024, 06:08
Francois Gallard
Join Date: Mar 2010
Location: Toulouse, France
Posts: 43
Rep Power: 16
fgal is on a distinguished road
Thanks for this information, this is useful, I have a similar problem.

How is the adjoint handled when using a custom shape parametrization?

Is there a way to output the derivatives of the functions with respect to the surface nodes coordinates in order to compute the gradient with respect to the design variables externally?

Best regards
fgal is offline   Reply With Quote


mesh deformation, parsec, su2

Thread Tools Search this Thread
Search this Thread:

Advanced Search
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are Off
Pingbacks are On
Refbacks are On

Similar Threads
Thread Thread Starter Forum Replies Last Post
Any questions about Runge-Kutta methods Runge_Kutta Main CFD Forum 33 September 9, 2019 16:32
shape optimization problem yugang881 SU2 Shape Design 3 December 14, 2017 05:26
Airfoil Shape Optimization using gradient based methods jaiswal Main CFD Forum 1 April 10, 2014 11:22
comments on FDM, FEM, FVM, SM, SEM, DSEM, BEM kenn Main CFD Forum 2 July 18, 2004 18:28
I just wonder why "SIMPLE" Junseok Kim Main CFD Forum 21 May 20, 2001 08:47

All times are GMT -4. The time now is 04:29.