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 1 (217.56 KiB) Viewed 42 times
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
Join a community of subject matter experts. Register for FREE to view solutions, replies, and use search function. Request answer by replying!