1. Calculate the static thrust of the rocket, turbojet and turbofan engine schematically given in the figures below. (T thrust force is enough to keep the engines immobilized. Exhaust mass flow rates of rocket and turbojet engines are 40 kg / s. For the turbojet engine, the air-fuel flow rate is 50, the gas velocity at the exhaust nozzle exit plane is 500 m/s, and the exhaust pressure and ambient pressure are equal. The rocket nozzle exit cross section area is 2 m² and the propellant velocity is 300 m/s, the exhaust pressure is 0.140 MPa, the environmental pressure is 0.101 MPa. For the turbofan engine, the mass flow rate at the inlet of the air is 100 kg/s and the fuel flow rate is 2 kg/s. In the fan, the thrust of 50% of the thrust value of the turbojet engine given in (b) option occurs. Exhaust pressure and ambient pressure are equal. Air; it leaves the fan and the main nozzle at a speed of 500 m/s.) Propellant inlet (a) Rocket Fuel inlet Fuel inlet Pa Pa Turbojet Turbofan (b) (c)