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Wrong Drag and Lift Coefficient when changing AoA

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Old   November 19, 2013, 02:26
Unhappy Wrong Drag and Lift Coefficient when changing AoA
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I'm trying to calculate Drag and Lift Coefficient of NACA 2415 airfoil. When flow with velocity of 10m/s passes over the airfoil with angle of attack (AOA) = 0, the CD and CL is as same as the data giving in Theory of wing sections.
Unfortunately, when I change the AOA, the result is terrible, even the CD is negative.
I try two model (k-e and SST) with Y+ calculated according to ,but it does not change
Please give me some explain and solution for this problem
Thanks in advance.
PS: I attack my mesh for convenience
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Old   November 27, 2013, 14:00
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recheck your drag calculation components in Monitors. Try to visualize the components according to your coordinate system.
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