Question: Under low-speed incompressible flow conditions, the pressure coefficient at a given point on an airfoil is -0.54. Calculate Cp at this point when the free

Under low-speed incompressible flow conditions, the pressure coefficient at a given point on an airfoil is -0.54. Calculate Cp at this point when the free stream Mach number is 0.58, using

(a) The Prandtl-Glauert rule

(b) The Karman-Tsien rule

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