Question: Problem 5.13 Consider a NACA 1412 airfoil at an angle of attack of a = 4. If the free-stream Mach number is M =

Problem 5.13 Consider a NACA 1412 airfoil at an angle of attack

Problem 5.13 Consider a NACA 1412 airfoil at an angle of attack of a = 4. If the free-stream Mach number is M = 0.8, calculate the lift coefficient.

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