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Statement of a problem № 42418

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A single-stage rocket is fired from rest from a deep-space platform, where gravity is negligible. If the rocket burns its fuel in 50.0 s and the relative speed of the exhaust gas is v~ = 2100 m/s, what must the mass ratio mo/m be for a final speed v of 8.00 km/s (about equal to the orbital speed of an earth satellite)?




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