CFD vs Experimetal Results for Aerofoil
Hi, I'm comparing experimental results obtained for a NACA 0012 aerofoil in a wind tunnel with CFD results ran on Fluent.
The CFD model was a very simple 2D, steady time, incompressible model using k-epsilon and standard wall functions. BC's were a pressure inlet and outlet and symmetry on upper/lower surfaces or fluid domain.
Despite the low inlet gauge pressure of 215pa, I'm getting pressure readings on the surface of the aerofoil that lead to pressure coefficients greater than +ve 1 on the pressure surface at 9 deg and 12 deg incidence.
Can anyone explain why this may be happening? Is it a problem with the wall function?
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