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Question: calculate the thrust of a rocket and turbojet engine see...

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Calculate the thrust of a rocket and turbojet engine (see the figures below). Both engines are stationary (u 0) and their total mass flow rate at exit is 120 lbm/sec be sure to include the acceleration of gravity to achieve the correct units of thrust (Ib)]. The surrounding ambient pressure is 14.7 psia. For the turbojet engine, the ratio of the air to fuel mass flow rate is 50:1 and the exit velocity is 1500 ft/sec. The exit pressure of the turbojet engine is the same as the ambient pressure. The rocket engine mass flow rate is only the added fuel (or propellant) with an exit velocity of 9000 ft.2 through the exit area 2 ft.. The exit pressure of the rocket engine is 22.5 psia. Fuel flow Propellant now Pa Le lle Ae Pa TURBOJET ROCKET

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