## Description

__Problem:__

__Problem:__

A turbojet engine takes 50 (kg/sec) of air and propels an aircraft with uniform flight speed of 880 (km/hr). Isentropic enthalpy change for the nozzle is 188.28 (kJ/kg) and its velocity coefficient (being a ratio of the velocity of the jet relative to the aircraft speed over the exit velocity of gases) is 0.96. The fuel/air ratio is 1.2 percent. Combustion efficiency is 95 percent, and the calorific value of fuel is 4.393 x 10^{4}(kJ/kg).

__Find: __

__Find:__

(1) the thermal efficiency of the engine,

(2) the fuel flow in (kg/hr) and specific fuel consumption,

(3) the thrust power, propulsive efficiency, and overall efficiency.

__Given Data:__

__Given Data:__

- ṁ
_{a}= 50 kg/sec - V
_{aircraft}= 880 km/hr = 244 m/sec - Isentropic enthalpy change for Nozzle h
_{5}– h_{6s}= 188.28 kJ/kg - Fuel/Air = 1.2 % = 0.012
- ṁ
_{f}/ṁ_{a }= 0.012 - Combustion efficiency η
_{combustion }= 95 % - Calorific Value of fuel CV
_{f}= 4.393 x 10^{4}kJ/kg

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