Engineering, 14.09.2019 01:30 kamand10

Acompressor blade design tested in a cascade is found to choke with an inlet mach number of 0.9 when the inlet flow angle is 52 deg. if the ratio of the throat area to the frontal area, a*/h1s, for the cascade is).625, calculate the loss of stagnation pressure between the far upstream and the throat and express this as a loss coefficient. give your comments on what could cause this loss.

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Acompressor blade design tested in a cascade is found to choke with an inlet mach number of 0.9 when...