Consider an airplane flying with a velocity of 60 at a standard altitude of 3 km. At a point on the wing, the airflow velocity is 70 . Calculate the pressure at this point.

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The type of calculation in Prob. 4.3 is a classic one for low-speed, incompressible :flow; that is, given the free-stream pressure and velocity and the velocity at some other point in the :flow, calculate the pressure at that point In a high-speed compressible :flow, Mach number is more fundamental than velocity. Consider an airplane :flying at Mach 0.7 at a standard altitude of3 km. At a point on the wing, the airflow Mach number is 1.1. Calculate the pressure at this point. Assume an isentropic :flow. Prob. 4.3 Consider an airplane flying with a velocity of 60 at a standard altitude of 3 km. At a point on the wing, the airflow velocity is 70 . Calculate the pressure at this point. Assume incompressible flow.

 

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