Question: A spacecraft rocket uses pressurized nitrogen gas ( = 1.4 = constant, M = 28 g/gmol, R = 297 m2/s2K) for propellant (this is a

A spacecraft rocket uses pressurized nitrogen gas (\ = 1.4 = constant, M = 28 g/gmol,\ R = 297 m2/s2K) for propellant (this is a cold gas thruster). The pressure in the nitrogen\ tank will decrease during the mission, but assume for simplicity that the gas temperature in the\ tank remains constant with the value T0 = 300 K.\ The rocket nozzle is designed to give a pressure ratio of pe/pt = 10-4. Determine:\ a) the nozzle gas exhaust temperature, Te (K), and the nozzle gas exhaust velocity, ue (m/s);\ b) the nozzle area ratio, Ae/At;\ c) the equivalent exhaust velocity, Veq (m/s), and the specific impulse, Isp (s)

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