In a rocket motor, liquid hydrogen and liquid oxygen enter into combustion chamber at a rate of 1.2 kg/s and 7 kg/s respectively. After combustion, the exhaust gas leaves the nozzle with diameter of 14 cm at 870 k and 1.2 atm. For this condition, the exit velocity of exhaust gases would be: (assume the exhaust gases are perfect with m.Wt of 28 kg/kmol)
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