|June 1, 2010, 05:37||
lift drag naca
Join Date: Jan 2010
Location: Germany, Trier
Posts: 31Rep Power: 7
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
Last edited by chelvistero; June 1, 2010 at 05:56.
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