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Search: Posts Made By: chelvistero
Forum: OpenFOAM June 1, 2010, 05:37
Replies: 0
Views: 1,426
Posted By chelvistero
lift drag naca

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...
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