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a a 1. Consider a rocket engine operating with a fuel mixture with y 1.2 and molecular weight of 16 kg/kmol. At a given flight altitude pe 0.5 atm (abs), pc 50 atm (abs) and T. 4000 K. The total propellant flow rate is 1000 kg/s and is maintained at this value for all flight condition. Here, subscript e and c denote respectively, the nozzle exit and combustion chamber conditions. S
(c) Derive an expression for Cs in terms of known parameters in the problem including the area ratio Ae/A*. Here, A* is the throat area. (d) How does Cr vary with A/A* and pe/pe? (e) Sketch Cr versus Ae/A* for the conditions in this problem. Plot linear (CT) versus log(Ae/A*) for a range of Ae/A* from 1-200. What is the maximum Cr? a