I need the answer as soon as possible Q3) A turbojet engine is operates at altitude where temperature and pressure are 216K, 60kParespectively. The air craft speed is 250m/s and the engine data is given below. Assume that,properties of the combustion gas same as those of air and no stagnation pressure losses inthe inlet diffuser.Combustion• The stagnation temperature at the turbinechamber3inlet=1500KToa PeaTes PaaTemperature drop at the turbine= 205 C• Calorific valve of the fuel= 42MJ/ KgTurbine efficiency= 0.9• Compressor efficiency 0.8• Combustion efficiency= 0.95Exhaust Nozzle efficiency =0.93Stagnation pressure at the turbine entry:(Po3) = 0.97 x Po2AirCompressorTurbineNozzieExhaustTAT. PeIntetdifuserTor. PorToe PosCalculate:1- Air to fuel ratio2- Exhaust nozzle pressure3- The velocity of the exhaust jet4- Thrust force develops if the inlet diffuser area is 0.5m25- Propulsive efficiency, specific thrust

Given: Ti=216 K Pi=60 kPa Air craft speed =250 m/s To determine: Air to fuel ratio Exhaust nozzle…

Answered: 1- Air to fuel ratio 2- Exhaust nozzle…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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1- Air to fuel ratio 2- Exhaust nozzle pressure 3- The velocity of the exhaust jet