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February 18, 2010, 11:36
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problem with stall in naca 0012 airfoil
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Member
thanos
Join Date: Oct 2009
Posts: 30
Rep Power: 15  |
Hello!
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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