Question: Problem 0 5 . 0 1 3 - Calculate lift coefficient for an airfoil Consider a NACA 1 4 1 2 airfoil at an angle

Problem 05.013- Calculate lift coefficient for an airfoil
Consider a NACA 1412 airfoil at an angle of attack of \(2^{\circ}\). If the free-stream Mach number is 0.8, calculate the lift coefficient. Refer to the Appendix graph given below for standard values.
Problem 0 5 . 0 1 3 - Calculate lift coefficient

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