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chelvistero June 1, 2010 05:37

lift drag naca
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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!
Please help

Thanks in advance

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