Can I use wall functions for calculating drag of a supersonic aircraft?
 

Hello,

as the title already says: I am trying to simulate an aircraft flying supersonic (mach 1.8 ) in high altitude : since the geometry is quite complex, I get a lot of bad cells when I use prism layers.

In order to avoid to go down to y+=1 and having lots of cells I am wondering if I can use wall functions of the k w sst model by trying to achieve y+>30 ?

Will this give me an accurate solution regarding the calculation of the drag? The shock system will have a fine resolution in order to capture the effects.

Thank you for your feedback

Best regards
CellZone