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An aircraft flies with a Mach number Ma1=0.921 at an altitude of 7021 m where the...

An aircraft flies with a Mach number Ma1=0.921 at an altitude of 7021 m where the pressure is 42.1 kPa and the temperature is 242.1 K. Calculate the stagnation properties (static temperature, pressure, density), cross-section areas A1 and A2=? at the inlet and outlet of the diffuser. The diffuser at the engine inlet has an exit Mach number of Ma2=0.3. For a mass flow rate of 32.1 kg/s, determine the static pressure rise across the diffuser and the exit area.

Solve the problem by making the necessary assumptions and drawing the schematic figure.

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