The rocket equation given by Delta V = Ve ln (Mo/M) says that Ve is the exhaust velocity of the rocket.(adsbygoogle = window.adsbygoogle || []).push({});

The orbital velocity for Low Earth Orbit is about 7.8 Km/s. How then, is this velocity attained by a rocket which is fuelled only by a bipropellant rocket engine producing an exhaust velocity of 4.4 Km/s. Using conservation of momentum, the heavier mass of the rocket wont reach the velocity of the exhaust?

Pls explain to me how this works..

THanks in advance

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# Rocket equation exhaust velocity question

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