FLUID MECHANICS An aircraft flying at an altitude of 5 km with a Mach number of...

FLUID MECHANICS

An aircraft flying at an altitude of 5 km with a Mach number of 0.15.

Calculate the velocity of the aircraft? (+1 point)

Calculate the pitot tube measurement reading at the nose using Bernoulli (+1 point) and Isentropic equations (+1 point) separately. Compare them!!!

Calculate pressure coefficient (Cp) at the nose(stagnation) point. (+0.5 point)

Calculate the pressure coefficient (Cp) at the point where Mach number reaches 0.25 (+1 point)

Expert Solution

samet mamat answered 1 year ago

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