The space shuttle main engine consumes approximately \(140.3 \mathrm{~kg} / \mathrm{s}\) of liquid hydrogen and \(374.2 \mathrm{~kg} / \mathrm{s}\) of liquid oxygen at full power. The overall ratio of hydrogen to oxygen on a mole-basis is approximately 6:1 so the combustion products are a gaseous mixture of water and excess hydrogen. The latter is used to cool the engine. The nozzle expands the hot, high pressure, gaseous combustion products to produce thrust-a process we will learn a lot more about later. If the temperature and pressure at the nozzle's exit are \(12.7 \mathrm{kPa}\) and \(390 \mathrm{~K}\), respectively, and the effective diameter of the nozzle exit is \(2.16 \mathrm{~m}\), find the speed of the gas mixture at the nozzle exit.

Transcribed Image Text:

mos Injector plate Combustion chamber Injector plate Combustion chamber Control surface Nozzle K Vexil Nozzle Az exit Exit plane Rout