Question

Consider the NACA 0012 airfoil at zero angle of attack. The minimum

pressure coefficient, measured in a wind tunnel at low speed, is -0.56.

Estimate the critical Mach number of the NACA 0012 airfoil at zero

angle of attack using the Prandtl-Glauert rule. Where γ = 1.4.​

Answer 1

Answer:

not have any idea about this question