Question: In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an NACA 0012 airfoil is 0.41. Estimate the critical Mach number

In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an NACA 0012 airfoil is —0.41. Estimate the critical Mach number for this airfoil, using the Prandtl-Glauert rule.

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