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The Mach number at inlet and exit of a supersonic diffuser are 2.5 bar and 1.2 respectively. The air inlet has a pressure of 80
The Mach number at inlet and exit of a supersonic diffuser are 2.5 bar and 1.2 respectively. The air inlet has a pressure of 80 kPa and -3C. If the mass flow rate of the air is 120 kg/s, find i) stagnation pressure and temperature of air ii) exit area iii) static pressure and temperature of air at exi
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