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)
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Transcribed Image Text: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 kgm/s
Molecular weight (gas mixture)
Specific heat ratio (gas mixture) = 1.22
Universal gas constant = 8,314 J/ (kg/mol) (K)
= 16 mol
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