Airfoil shape design
 

Hello everyone.



I am using SU2 for the optimization of an airfoil (subsonic, turbulent case). The airfoil (BE 123-155) will be used as a GT-vehicle spoiler, thus in ground effect. The objective function is the CL and there are no constraints for DRAG end MOMENTUM.

The problem is that after some iterations the thikness reduces almost to zero in some parts. I have tried using OPT_CONSTRAINT=( AIRFOIL_THICKNESS > ### ) because that's what they do in in the tutorials but the problem is still happening.
Any advice??


Thanks to everyone

Hi,
Airfoil thickness is the maximum thickness, as in 12% for the NACA0012.
The most effective way is to limit the range of the variables so that it is not possible for the thickness to become to low.

Thanks a lot!