A turbojet engine is designed to generate 30,000 lbs of thrust at a take-off velocity of 190 ft/s at sea level. At take-off, the gas velocity at the exit of the engine (relative to the engine) is 1600 ft/s. The fuel-air ratio is 0.025. The exit pressure is equal to the ambient pressure. Calculate the area of the engine inlet required to obtain this thrust. Note: you can assume that the density and velocity of the air entering the inlet are the freestream density at sea level, and the aircraft velocity, respectively.