A turbo jet engine is propelling an aircraft at a speed of 239.6 m/s and has the following data. Mass flow rate of air = 45 kg/s, mass flow rate of fuel = 2.65 kg/s, thrust produced = 50 kN. Determine the specific thrust, thrust specific fuel consumption, exhaust jet velocity, heat supplied and propulsive efficiency. Take the calorific value of fuel as 42800 kJ/kg and assume the exit pressure is equal to ambient pressure.
