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.