A liquid fueled 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 2400oC. Find the temperature of the gases at 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.