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NACA 4412 airfoil for Cd

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Old   November 30, 2011, 11:00
Default NACA 4412 airfoil for Cd
Join Date: Jan 2011
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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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