Please, solve this problem in detail:

Consider the pumps necessary to supply a booster engine of 8.5MN of thrust. The engine consumes liquid oxygen and RP-1 in the mass flow rate ratio 2.5:1. The flame temperature is 3300K, the chamber pressure 10MPa, and the specific impulse 307 sec. Densities of liquid oxygen and RP-1 are 1140 and 750kg/m3, respectively. What total shaft power is necessary, assuming a propellant tank pressure of 0.30MPa ? Make an allowance for the pressure drop across an injector with a discharge coefficient of 0.98 and an injector area of 0.029m2 for both the oxidizer and fuel manifolds. Assume the pump is isentropic