ch09-p077 - 77. (a) The thrust of the rocket is given by T...

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77. (a) The thrust of the rocket is given by T = Rv rel where R is the rate of fuel consumption and v rel is the speed of the exhaust gas relative to the rocket. For this problem R = 480 kg/s and v rel = 3.27 × 10 3 m/s, so T = × 480 327 10 157 10 36 kg s m s N. bg c h .. (b) The mass of fuel ejected is given by M fuel = Rt Δ , where Δ t is the time interval of the burn. Thus, M fuel = (480 kg/s)(250 s) = 1.20
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