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November 30, 2011, 10:00
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NACA 4412 airfoil for Cd
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Member
John
Join Date: Jan 2011
Posts: 69
Rep Power: 15  |
The drag coefficient is negative at high angle of attacks!!
however at 0 angle of attack it seems to be OK. the lift coefficient is acceptable and good at all AOA. What is the problem. I would say its my inputs when in the boundary conditions for pressure farfield; i have it as X component= cos (10) and Y component = sin (10) please help me |
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