The main engines of the Saturn V rocket (used for the Apollo and Skylab missions) burn a fuel consisting of a mixture of kerosene and liquid oxygen. The exhaust from the combusted fuel exits the rocket engine at a velocity of 3.1 10^3 m/s. The mass of the rocket at liftoff is 2.45 10^6 kg, of which 1.70 10^6 kg are kerosene and liquid oxygen. (a) If the rocket starts from rest, what would the final velocity of the rocket be (ignoring the effects of gravity)? (b) In order to achieve a total thrust of 3.3 10^7 N, at what rate must the engines of the Saturn V consume fuel?