how to calculate the pressure coefficient of a wing
I want to simulate the ONERA M6 Wing. But do not know how to calculate the pressure coefficient for the upper and lower surface of the airfoil.
Does anyone has idea how to realize it?
Thanks a lot in advance!
As far as I know there is now tool at present that lets you calculate Cp in OF. (But if you come across one, do post it here.) However you can add code to calculate Cp in your solver using "Function Objects". Just search this on google and you would get all the details.
Moreover you can simply write those lines in your solver and recompile it.
DO you know how to creat an 1D data file by intersecting a plane in the boddy or wing?
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