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A 600 kg rocket is set for a vertical firing. If the exhaust speed is 1000 ms-1 the mass of the gas ejected per second to supply the thrust needed to overcome the weight of rocket is
(a) 1/7.6 kg s-1
(b) 58.6 kg s-1
(c) 6 kg s-1
(d) 76.4 kg s-1
(c) Thurst = (udM )/dt=mg => dM/dt=mg/u
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