Fuel is consumed in a rocket at the rate of `200 kg//s` . What is the thrust experienced by the roket if exhaust gases are ejected at a speed of `45 km//s` ?

Explanation

Here , ` (dm)/(dt) = 200 kg //s , u= - km//s =- 45 xx 10^(3) m//s`
Thrust on the rocket , `F = ? `
As ` F = -u ((dm)/(dt)) :. F = - (-45 xx 10^(3)) xx 200 = 9 xx 10^(6) N` .