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?ex = 2100 m/s, what must the mass ratio ?m?0/?m? be for a final speed v? of 8.00 km/s (about equal to the orbital speed of an earth satellite)?

Solution 65E The relation between the mass ratio m0 and the final speed (v) is given by, m v = v exln m 0…..(1) , here v xs the gas exhaust speed. m Given that, v = 8.00 km/s = 8000...