A liquid propellant rocket engine operates on liquid oxygen and kerosene. It burns propellant ata mixture ratio of 2.3 and with the combustion chamber pressure of 55 atm. It expels

mass at a rate of 500 kg/s. Now answer the following questions: Exhaust pressure = Ambient pressure Combustion temperature, Tc = 3,470K Molar mass of the exhaust, M = 21.40 g/mole Specific heat ratio, k = 1.221 If the nozzle is expanded to operate at sea level, calculate the exhaust gas velocity relative tothe rocket. Calculate nozzle's throat's pressure, temperature and area. Calculate the exit Mach number, exit area and section ration of the nozzle.