Calculate the nozzle exit area required and the thrust

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Reference no: EM13613775

the stagnation temperature and pressure in the jet pipe of a turbojet engine are found to be 2.4 bar and 1000k, under take-off conditions when ambient pressure and temperature are 1.01 bar and 288k. The mass flow rate in the engine is 23[kg/s]. A converging-only is used in this application. Calculate the nozzle exit area required and the thrust produced by this turbojet assuming that the expansion process in the nozzle is isentropic.

Reference no: EM13613775

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