Can I use wall functions for calculating drag of a supersonic aircraft? -- CFD Online Discussion Forums

March 31, 2022, 09:21	Can I use wall functions for calculating drag of a supersonic aircraft?	#1
CellZone Member Join Date: Apr 2016 Posts: 90 Rep Power: 10	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

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