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For a rocket traveling at 700 m/s having an exhaust velocity of 1.4 km/s, exhaust gas density of 0.3 kg/m3, nozzle throat diameter of 0.14 cm and nozzle exit diameter of 25 cm, find the total mass flow rate of the propellants.

For a rocket traveling at 700 m/s having an exhaust velocity of 1.4 km/s, exhaust gas density of 0.3 kg/m3, nozzle throat diameter of 0.14 cm and nozzle exit diameter of 25 cm, find the total mass flow rate of the propellants. Correct Answer 20.62 kg/s

Mass flow rate of the propellants is the same as the mass flow rate of the rocket exhaust jet exiting the nozzle. That will be equal to the product of exhaust gas density, nozzle exit area, and exhaust velocity. m = ρ Ae ue = 0.3 x π/4 x (25 x 10-2)2 x 1400 = 20.62 kg/s.

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