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problem with stall in naca 0012 airfoil

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Old   February 18, 2010, 11:36
Default problem with stall in naca 0012 airfoil
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I try to simulate naca 0012 in a Re=2*10^6 , u=40m/s and c=1. I use Spalart-allamaras turbulence model.
For this Re number the airfoil stalls in angle of attack=14.
I have made many different meshes with y+<3 but none of them has been effective.
The problem i face is that although for angles up to 14 i calculate Cl with minimun divergence, in bigger angles (15,16...) the Cl continues to increase instead of falling.
Is anything that i am doing wrong?
Please help!
Thanks in advance!
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