, calculate the (a) specific impulse, (b) exit velocity, (c) mass flow, (d) thrust, and (e) throat area..

Consider a rocket engine in which the combustion chamber pressure and temperature are 30 and 3756 K, respectively. The area of the rocket nozzle exit is 15 Jii2 and is designed so that the exit pressure exactly equals ambient pressure at a standard altitude of25 km. For the gas mixture, assume that r= 1.18 and the molecular weight is 20. At a standard altitude of25 km, calculate the (a) specific impulse, (b) exit velocity, (c) mass flow, (d) thrust, and (e) throat area.

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