Ajet aircraft is traveling at 291 m/ s in horizontal flight. the engine takes in air at a rate of 63.8 kg/s and burns fuel at a rate of 1.21 kg/s. the exhaust gases are ejected at 667 m/s relative to the aircraft. find the thrust of the jet engine and the delivered power.

thrust = 24795.87 N

Power  = 7.215 MW

Explanation:

given data

The speed of the jet v = 291 m/s

The air intake is dMa/dt = 63.8 kg/s

The fuel burn rate is dMf/dt = 1.21 kg/s

The speed of the exhaust gas is u = 667 m/s

to find out

thrust of the jet engine and the delivered power

solution

first we get here rate of mass change in the rocket that is  

rate of mass change dM/dt = 63.8  + 1.21

rate of mass change dM/dt = 65.01 kg/s

and

The thrust on the rocket will be here

thrust T = (dM/dt) u - (dMa/dt) v       1

thrust T = (65.01) 667 - (63.8) 291

thrust T = 24795.87 N

and

now the power of the rocket will be here

Power  = speed × thrust        2

Power  = 291  × 24795.87

Power  = 7.215 MW

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