NACA 4412 airfoil for Cd
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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