Consider a rocket engine in which the combustion chamber pressure and temperature are 30 atm and 3756 K, respectively. The area of the rocket nozzle exit is 15 m2 and is designed so that the exit pressure exactly equals ambient pressure at a standard altitude of 25 km. For the gas mixture, assume that γ= 1.18 and the molecular weight is 20. At a standard altitude of 25 km, calculate the (a) specific impulse, (b) exit velocity, (c) mass flow, (d) thrust, and (e) throat area.
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