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In a rocket engine, liquid fuel and liquid oxygen are fed into the combustion chamber as shown below. The hot exhaust gases of the combustion flow out of the nozzle at high exit velocity of 1000 m/s. Assume the pressure and temperature of the gases at the nozzle exit are 100 kPa and 800 K, respectively. The nozzle has an exit area of 0.05 m2. Determine the mass flow rate of the fuel if the oxygen and fuel ratio is set at 5 to 1. Also, assume the exhaust gases can be modeled as an ideal gas with R=1 kJ/kg.K.