The fuel in a rocket is burnt at the rate of 50 kg/s and the gases are ejected at the rate of `6 xx 10^4m/s` with respect to the rocket, What is the thrust developed?

Explanation

Thrust = `v(dm)/dt`, V is the exhaust velocity of the ejected gases w.r.t
the rocket = `6xx10^4xx50 = 3xx10^6N`.