Working on a project that required a EES software in engineering thermodynamics

EES software is required for this project, Mechanical Engineering Thermodynamics 27-1 A turbojet engine propels an aircraft at a speed of 535 miles per hour through still air at 6.5 psia, 9°F. The inlet diameter of the diffuser of the engine is 5.25 ft. The pressure ratio of the engine is 13 and the temperature at the turbine inlet is 1035°F. Air leaves the nozzle of the engine at 6.5 psia. Analyze engine performance with 100% compressor and turbine efficiency and then with 85% compressor as well as turbine efficiency. For the real and ideal turbojet engine, determine and compare the following: (a) The velocity at the exit of the nozzle (mph) (b) The propulsive force (thrust) of the engine (lbf) (c) The heat transfer rate required at the combustion chamber (Btu/hr) (d) The propulsive power of the engine (hp) (e) The propulsive efficiency of the engine Note: Analyze this engine using the real-fluid properties of air (fluid name = ‘air_ha’).