ideal turbojet with an afterburner flies at 22,000 ft with a Mach numher of 0.88

ideal turbojet with an afterburner flies at 22,000 ft with a Mach numher

of 0.88. It ingests 192 lbm/s of air, and the compressor pressure ratio 

The fuel has a heating value of 17,900 Btu/Ibm. The primary burner »nd

afterburner exit total temperatures are 2350 and 2980 OR, respectively. (a)

Find the developed thrust, dimensionless thrust, and TSFC. (b) Compare

these parameters with those of the nonafterburning case.

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The Mach number ofan ideal turbojet that flies at 27,000 ft is 0.82. The airflow is 205 lbm/s

The Mach number ofan ideal turbojet that flies at 27,000 ft is 0.82. The airflow

is 205 lbm/s, and the burner total temperature is 2550 OR. The heating value of

the fuel is 17,700 Btu/Ibm. Ifthe thrust is to be maximized, find the resulting

compressor ratio and TSFC. How sensitive is the thrust to this pressure ratio

that is, if the pressure ratio is increased by 4 percent, how much will the

thrust drop? How much will the TSFC drop? Comment.

manual solution Fundamentals of Jet Propulsion with Applications by Flack. R.D

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The Mach number ofan ideal turbojet that flies at 27,000 ft is 0.82. The airflow

is 205 lbm/s, and the burner total temperature is 2550 OR. The heating value of

the fuel is 17,700 Btu/Ibm. Ifthe thrust is to be maximized, find the resulting

compressor ratio and TSFC. How sensitive is the thrust to this pressure ratio

that is, if the pressure ratio is increased by 4 percent, how much will the

thrust drop? How much will the TSFC drop? Comment.

An ideal turbojet powers a Mach 0.92 aircraft that requires 15,500 lbf ofthrust at sea level

An ideal turbojet powers a Mach 0.92 aircraft that requires 15,500 lbf ofthrust

at sea level. The compressor ratio is 16.4, and the exit total temperature from

the combustor is 2450 OR. The heating value of the fuel is 18,100 BtuJlbm.

Find the required airflow. How large will the nozzle exit diameter be? What

is the resulting TSFC and dimensionless thrust?

manual solution Fundamentals of Jet Propulsion with Applications by Flack. R.D

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An ideal turbojet powers a Mach 0.92 aircraft that requires 15,500 lbf ofthrust

at sea level. The compressor ratio is 16.4, and the exit total temperature from

the combustor is 2450 OR. The heating value of the fuel is 18,100 BtuJlbm.

Find the required airflow. How large will the nozzle exit diameter be? What

is the resulting TSFC and dimensionless thrust?

An ideal turbojet ingests 192 lbm/s of air at an altitude of 22,000 ft. It flies at

An ideal turbojet ingests 192 lbm/s of air at an altitude of 22,000 ft. It flies

at a Mach number of 0.88, and the compressor pressure ratio is 17. The fuel

has a heating value of 17,900 Btu/Ibm, and the burner exit total temperature

is 2350 OR. Find the developed thrust, dimensionless thrust, and TSFC

manual solution Fundamentals of Jet Propulsion with Applications by Flack. R.D

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Eng.Yazan Jarrah

An ideal turbojet ingests 192 lbm/s of air at an altitude of 22,000 ft. It flies

at a Mach number of 0.88, and the compressor pressure ratio is 17. The fuel

has a heating value of 17,900 Btu/Ibm, and the burner exit total temperature

is 2350 OR. Find the developed thrust, dimensionless thrust, and TSFC

A turboprop operates at sea level and moves at 783 ft/s. It ingests 30 lbm/s

A turboprop operates at sea level and moves at 783 ft/s. It ingests 30 lbm/s

of air and has negligible fuel flow. The area of the exit is 290 in.2• The exit

pressure is 14.7 psia, and the exit velocity is 625 ft/s. The thrust from the

propeller is 2517 lbf. Find the total developed thrust.

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A turbofan operates at sea level and moves at 893 ft/s. It ingests 150 lbmls of air into the core and 2.2 times this

A turbofan operates at sea level and moves at 893 ft/s. It ingests 150 lbmls of

air into the core and 2.2 times this amount into the fan, which all is mixed into

the core flow. The fuel flow is negligible. The exit area is 851 in.2• The exit

pressure is 18.4 psia, and the exhaust velocity is 1435 ftJs. Find the thrust.

manual solution Fundamentals of Jet Propulsion with Applications by Flack. R.D

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A turbofan operates at sea level and moves at 893 ft/s. It ingests 150 lbm/s of air into the core and

A turbofan operates at sea level and moves at 893 ft/s. It ingests 150 lbm/s

of air into the core and 2.2 times this amount into the fan, which all exits

through the fan exhaust. The fuel flow is negligible. The exit areas ofthe fan

and core are 336 and 542 in.2, respectively. The exit pressures from the fan

and core are 14.7 and 15.8 psia, respectively. The exhaust velocities from

the fan and core are 2288 and 1164 ftJs, respectively. Find the thrust. What

proportions arise from the fan and core?

manual solution Fundamentals of Jet Propulsion with Applications by Flack. R.D

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