static pressure

An aircraft flies with a Mach number Ma1 = 0.8 at an altitude of 7000 m where the pressure is 41.1 kPa and the temperature is 242.7 K. The diffuser at the engine inlet has an exit Mach number of Ma2 = 0.3. For a mass flow rate of

65 kg/s, determine the static pressure rise across the diffuser and the exit area.

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