Liquid oxygen and liquid hydrogen are both fed into the combustion chamber of a liquid-fueled rocket engine at a rate of 5 kg/s (each). The products of combustion from this chamber are exhausted through a convergent-divergent nozzle. The exit plane of this exhaust nozzle has a diameter of 0.3 m and the gases flowing through the nozzle are estimated to have a density of 0.1 kg/m3 on the exit plane. Estimate the gas velocity on the nozzle exit plane assuming one-dimensional flow on the the exit plane

Liquid oxygen I Combustion chamber Liquid hydrogen I Figure 2: Figure for Problem 2 1 Ue I I Control volume