Liquid hydrogen and oxygen are burned in a combustion chamber and fed through a rocket nozzle which exhausts at exit pressure equal to ambient pressure of 54 kPa. The nozzle exit diameter is 45 cm, and the jet exit density is 0.15 kg/m3. If the exhaust gas has a molecular weight of 18, estimate
(a) The exit gas temperature;
(b) The mass flow; and
(c) The thrust generated by the rocket.
NOTE: Sorry, we forgot to give the exit velocity, which is 1600 m/s.