Boeing 747 aircraft is powered by four CF-6 turbofan engines manufactured by General Electric Company. Each engine has the following data: 24.0 kN 125 kg/s 5.0 Thrust force Air mass flow rate Bypass ratio Fuel mass flow rate 0.75 kg/s Operating Mach number 0.8 10 km 223.2 K Altitude Ambient temperature Ambient pressure Fuel heating value 26.4 kPa 42,800 kJ/kg If the thrust generated from the fan is 75% of the total thrust and assume that the e pressures of the cold and hot streams are equal to the ambient pressure, determir (a) The jet velocities of the cold air and hot gases (b) The specific thrust (c) The thrust specific fuel consumption (TSFC) (d) The propulsive efficiency (e) The thermal efficiency (f) The overall efficiency

Boeing 747 aircraft is powered by four CF-6 turbofan engines manufactured by General Electric Company. Each engine has the following data: 24.0 kN 125 kg/s 5.0 Thrust force Air mass flow rate Bypass ratio Fuel mass flow rate 0.75 kg/s Operating Mach number 0.8 10 km 223.2 K Altitude Ambient temperature Ambient pressure Fuel heating value 26.4 kPa 42,800 kJ/kg If the thrust generated from the fan is 75% of the total thrust and assume that the e pressures of the cold and hot streams are equal to the ambient pressure, determir (a) The jet velocities of the cold air and hot gases (b) The specific thrust (c) The thrust specific fuel consumption (TSFC) (d) The propulsive efficiency (e) The thermal efficiency (f) The overall efficiency

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

Boeing 747 aircraft is powered by four CF-6 turbofan engines manufactured by
General Electric Company. Each engine has the following data:
24.0 kN
125 kg/s
Thrust force
Air mass flow rate
Bypass ratio
Fuel mass flow rate
5.0
0.75 kg/s
Operating Mach number 0.8
Altitude
10 km
Ambient temperature
Ambient pressure
Fuel heating value
223.2 K
26.4 kPa
42,800 kJ/kg
If the thrust generated from the fan is 75% of the total thrust and assume that the exit
pressures of the cold and hot streams are equal to the ambient pressure, determine:
(a) The jet velocities of the cold air and hot gases
(b) The specific thrust
(c) The thrust specific fuel consumption (TSFC)
(d) The propulsive efficiency
(e) The thermal efficiency
(f) The overall efficiency

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