Aerospace Engineering > GATE 2019 > Rocket Propulsion
For a rocket engine, the velocity ratio r is V_a/V_e, where V_a is the vehicle velocity and V_e is the exit velocity of the exhaust gases. Assume the flow to be optimally expanded through the nozzle. For r = 2, if F is the thrust produced and ṁ is the mass flow rate of exhaust gases, then, F/(ṁV_e) is _______.
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