Question: 1 . 5 Consider an airfoil at 1 2 angle of attack. The normal and axial force coefficients are 1 . 2 and 0 .

1.5 Consider an airfoil at 12 angle of attack. The normal and axial force coefficients are 1.2 and 0.03, respectively. Calculate the lift and drag coefficients.
1 . 5 Consider an airfoil at 1 2 angle of attack.

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