Calculate the static thrusts of the rocket and turbojet engine described in the figure. The thrust T is the force necessary to prevent horizontal movement of the engine. Both engines exhaust a mass flow of 40 kg/s. The ratio of air and fuel mass flowing into the turbojet is 50:1, and in its exhaust plane the velocity is 500 m/s and the pressure is the same as the ambient pressure. The rocket propellant exhausts at a velocity of 3000 m/s through the area of 0.2 m2. The pressure in the exhaust plane of the rocket is 0.15 MPa and ambient pressure is 0.101 MPa.