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Search: Posts Made By: parvez2683
Forum: FLUENT July 26, 2009, 20:25
Replies: 1
Views: 1,986
Posted By parvez2683
NACA0012 Cd and Cl values

Hi,
I am trying to simulate the flow over an airfoil NACA0012 with chord C=20mm and Velocity=7.3m/s, Re=10,000, laminar case.
I am not getting correct Cd and Cl at different angle of attack in...
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