Question

Consider the flow through a rocket engine nozzle. assume that the gas flow through the nozzle is an isentropic expansion of a calorically perfect gas. in the combustion chamber, the gas which results from the combustion of the rocket fuel and oxidizer is at a pressure and temperature of 15 atm and 2500 k, respectively; the molecular weight and specific heat at constant pressure of the combustion gas are 12 and 4157 j/kg.k, respectively. the gas expands to supersonic speed through the nozzle, with a temperature of 1350 k at the nozzle exit. calculate the pressure at the exit.

Answer 1

speed of tractor is =98
velocity of tractor is =23