- D A Rocket Engine Burning Liquid Oxygen And Kerosene Operates At A Combustion Chamber Pressure Of 30 Mpa The Nozzle I 1 (174.38 KiB) Viewed 20 times
(d) A rocket engine burning liquid oxygen and kerosene operates at a combustion chamber pressure of 30 MPa. The nozzle i
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(d) A rocket engine burning liquid oxygen and kerosene operates at a combustion chamber pressure of 30 MPa. The nozzle i
(d) A rocket engine burning liquid oxygen and kerosene operates at a combustion chamber pressure of 30 MPa. The nozzle is expanded to operate at the ambient pressure of 18 kPa. The specific impulse equals 340 s at this ambient pressure. Find its combustion chamber temperature. Adiabatic constant of the exhaust gas is 1.20, its molar weight is 23.2. [2 marks] (e) Find the mass flow rate of this engine described in Q1(d) if it produces 2.4 MN of thrust at the sea level (ambient pressure is 101 kPa). The exit diameter of the nozzle is 1.3 m. [2 marks] (f) A 15,000 kg spacecraft is in Earth orbit traveling at a velocity of 7,900 m/s. Its engine is burnt to accelerate it to a velocity of 11.2 km/s to reach the escape orbit. The engine expels mass at a rate of 125 kg/s and has a specific impulse of 430 s. Calculate the duration of the burn. [3 marks]
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