[RLangtry]

Has anyone managed to get tge recently announced 2D FFD optimization running yet? Is there an example problem (2d_mesh.su2, 2d_FFD.su2, .cfg) for the recently announced 2D FFD optimization capability? I've managed to get 3D FFD and 2D Hicks-Henne working correctly put after watching the latest Pointwise/SU2 workshop I'm struggling to get the 2D FFD running on an airfoil.

[fpalacios]

Originally Posted by RLangtry

Has anyone managed to get tge recently announced 2D FFD optimization running yet? Is there an example problem (2d_mesh.su2, 2d_FFD.su2, .cfg) for the recently announced 2D FFD optimization capability? I've managed to get 3D FFD and 2D Hicks-Henne working correctly put after watching the latest Pointwise/SU2 workshop I'm struggling to get the 2D FFD running on an airfoil.

Hi, Thanks for your interest in SU2

In principle, the procedure is analogous to the 3D case...

1) Add to the end of the .su2 file the following

FFD_NBOX= 1
FFD_NLEVEL= 1
FFD_TAG= 0
FFD_LEVEL= 0
FFD_DEGREE_I= 25
FFD_DEGREE_J= 1
FFD_PARENTS= 0
FFD_CHILDREN= 0
FFD_CORNER_POINTS= 4
1.1 -0.1
-0.1 -0.1
-0.1 0.1
1.1 0.1

2) Run SU2_MDC with

DV_KIND= FFD_SETTING
DV_MARKER= ( airfoil )
to generate a new .su2 (the one that you will use in the future with the complete FFD information - including parametric coordinates-)

3) add the FFD design variables to the .cfg file e.g.

DEFINITION_DV= ( 15, 1.0 | airfoil | 0, 0, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 1, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 2, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 3, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 4, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 5, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 6, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 7, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 8, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 9, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 10, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 11, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 12, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 13, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 14, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 15, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 16, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 17, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 18, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 19, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 20, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 21, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 22, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 23, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 24, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 25, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 0, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 1, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 2, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 3, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 4, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 5, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 6, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 7, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 8, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 9, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 10, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 11, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 12, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 13, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 14, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 15, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 16, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 17, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 18, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 19, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 20, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 21, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 22, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 23, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 24, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 25, 1, 0, 1.0 )

4) run the optimization

I hope this help,

Best Regards,
Francisco

[454514566@qq.com]

Originally Posted by fpalacios

Hi, Thanks for your interest in SU2

In principle, the procedure is analogous to the 3D case...

1) Add to the end of the .su2 file the following

FFD_NBOX= 1
FFD_NLEVEL= 1
FFD_TAG= 0
FFD_LEVEL= 0
FFD_DEGREE_I= 25
FFD_DEGREE_J= 1
FFD_PARENTS= 0
FFD_CHILDREN= 0
FFD_CORNER_POINTS= 4
1.1 -0.1
-0.1 -0.1
-0.1 0.1
1.1 0.1

2) Run SU2_MDC with

DV_KIND= FFD_SETTING
DV_MARKER= ( airfoil )
to generate a new .su2 (the one that you will use in the future with the complete FFD information - including parametric coordinates-)

3) add the FFD design variables to the .cfg file e.g.

DEFINITION_DV= ( 15, 1.0 | airfoil | 0, 0, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 1, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 2, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 3, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 4, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 5, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 6, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 7, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 8, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 9, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 10, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 11, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 12, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 13, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 14, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 15, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 16, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 17, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 18, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 19, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 20, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 21, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 22, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 23, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 24, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 25, 0, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 0, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 1, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 2, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 3, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 4, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 5, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 6, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 7, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 8, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 9, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 10, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 11, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 12, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 13, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 14, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 15, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 16, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 17, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 18, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 19, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 20, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 21, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 22, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 23, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 24, 1, 0, 1.0 ); ( 15, 1.0 | airfoil | 0, 25, 1, 0, 1.0 )

4) run the optimization

I hope this help,

Best Regards,
Francisco

Why I face an error:
'DV_PARAM: a design variable in the configuration file has the wrong number of parameters'
the .cfg is inv_NACA0015.zip