NUMBER 1; Consider a rocket engine burning hydrogen and oxygen; the combustion chamber (reservoir) pressure and temperature are 25 atm and 3517 K, respectively. The area of the rocket nozzle throat is 0.1m². The area of the exit is designed so that the exit pressure is equal to 0.01174 atm. Determine the exit area and exit velocity with the given parameters: Mass flow rate = 121.9 kg/s Molecular weight (gas mixture) = 16 mol Specific heat ratio (gas mixture) = 1.22 Universal gas constant = 8,314 J/ (kg/mol) (K)

NUMBER 1; Consider a rocket engine burning hydrogen and oxygen; the combustion chamber (reservoir) pressure and temperature are 25 atm and 3517 K, respectively. The area of the rocket nozzle throat is 0.1m². The area of the exit is designed so that the exit pressure is equal to 0.01174 atm. Determine the exit area and exit velocity with the given parameters: Mass flow rate = 121.9 kg/s Molecular weight (gas mixture) = 16 mol Specific heat ratio (gas mixture) = 1.22 Universal gas constant = 8,314 J/ (kg/mol) (K)