(Solved): 7. A rocket engine operates with a combustion chamber stagnation temperature of 3000K, a nozzle ...

7. A rocket engine operates with a combustion chamber stagnation temperature of 3000°K, a nozzle exit Mach number of 3.758 and exit pressure Pe of 101.3 kPa. For a nozzle throat diameter of 0.1 m determine the thrust (a) at sea level, where ambient pressure is the exit pressure pe (b) in vacuum Assume that the molecular weight of combustion products is 25 kg/kmol and 7= = 1.2.