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June 1, 2010, 05:37
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lift drag naca
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Member
Axel Söhngen
Join Date: Jan 2010
Location: Germany, Trier
Posts: 31
Rep Power: 16  |
Hello,
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 Last edited by chelvistero; June 1, 2010 at 05:56. |
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