Question: A liquid fuelled rocket is fired on a test stand. The rocket nozzle has an exit diameter of 30 cm, and the combustion gases leave the nozzle at a velocity of 3800 m/s and a pressure of 100 kPa, which is the same as the ambient pressure. The temperature of the gases in the combustion area is 2400°C. Find the temperature of the gases on the nozzle exit plane, the pressure in the combustion area, and the thrust developed. Assume that the gases have a specific heat ratio of 1.3 and a molar mass of 9. Assume that the flow in the nozzle is isentropic.