2. In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an aerofoil is -0.

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2 In Low Speed Incompressible Flow The Peak Pressure Coefficient At The Minimum Pressure Point On An Aerofoil Is 0 1 (48.91 KiB) Viewed 37 times

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AERODYNAMICS.
2. In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an aerofoil is -0.41. Estimate the critical Mach number, Mera for this aerofoil using Prandti-Glauert rule. [Ans: 0.74] Note: this problem can be solved graphically or analytically/by trial-and-error. The local pressure coefficient on an aerofoil surface at which the local Mach number is unity is the critical pressure coefficient, Cp,cr: 2 M Сper 7K 7-1) -1 (1+[(7-1)/2]M? 1+(7-1)/2 (y = 1.4 for air) DO