lift drag naca
I'm trying to simulate naca airfoil but getting not the right cd and cl.
Span of the naca is 0.8m and chord is 0.3m. With an angle of 0 degree I have an Aref of 0.052m^2 (0.8m * 0.065m). I use simpleFoam with LaunderSharmaKE turbulence model and yPlus ~ 1. Now I think about that my values in the controldict to calculate lift and drag are not right.
In blockMesh I have created one cell in z - direction with 0.8m (span).
I don't know what is wrong!
Thanks in advance
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