The nozzle of rocket engine is designed such that the exit pressure is 15kpa less than the atmospherique pressure of 101
Posted: Mon Jul 11, 2022 10:07 am
The nozzle of rocket engine is designed such that the exit pressure is 15kpa less than the atmospherique pressure of 101.325 kpa. The specific heat ratio is 1.25 and R for gases is 346 j/kgk. the combustion pressure and temperature are 1 Mpa and 3000 k . calculate the area ratio and exit velocity of the nozzle