At a point on the wing of the airplane, the velocity is 330 . Calculate the pressure at this point.

1. Derive an expression for the exit velocity of a supersonic nozzle in terms of the pressure ratio between the reservoir and exit po/pe. and the reservoir temperature T0. 2. Consider an airplane flying at a standard altitude of 5 km with a velocity of 270 . At a point on the wing of the airplane, the velocity is 330 . Calculate the pressure at this point.


 

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