The airplane has turbojet engine which produces 12.12 KN thrust at an altitude of 9150 m, where the ambient conditions are 32 kPa and 240 K. The pressure ratio across the compressor is 12 and temperature at the turbine inlet is 1400 K. The aircraft speed is 310 m/s. Assume ideal operation for all components; assume unchoked nozzle and constant specific heat in all processes, Cp = 1005 J/kgK. The heating value of the fuel is 42,700 kJ/kg. Determine (a) The fuel-to-air ratio (b) The velocity of the exhaust gases (c) The air mass flow rat
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