QUESTION 2 A compressor 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.

b) In a converging-diverging duct the flow conditions are such that a normal shock is formed at the exit of the diverging section. Upstream of the shock the flow conditions are as below. Mach number= '0.5198', Pressure= '311886.9' Pa and Temperature= '228.72' K. Obtain the Mach number, pressure, and temperature at the downstream of the shock. Assume standard air properties (y=1.4).

A turbojet engine with a convergent divergent nozzle expands the flow such that Po = 0.8 P, The engine has the following data at a flight Mach number of 1.5 : Te = 7.5 ,Tt4=1400 K, e. = et = 0.9 , y = 1.34 ,CP; = 1135 J/kg.K If the jet velocity is 1025 m/s, determine the flight altitude.

ASAP