An aircraft with a turbojet engine is flying with 250 m/s speed at an altitude where the density of air is 1 kg/m³. The inlet area of the engine is 1 m². The average velocity of the exhaust gases at the exit of the nozzle, with respect to the aircraft, is 550 m/s. Assume the engine exit pressure is equal to the ambient pressure and the fuel-air ratio is negligible. The uninstalled thrust produced by the engine at these conditions is _______ N (rounded off to the nearest integer).