Mass of the rocket is 50kg. Velocity of exhaust gases from the tail of the rocket is 5000m/s. The rate of consumption of feul per second just to rise the rocket from the ground
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F=v×dm /dt
here F = 50×10
so 500= 5000× dm/dt
dm/dt = 0.1
here F = 50×10
so 500= 5000× dm/dt
dm/dt = 0.1
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