2. A turbojet-powered aircraft cruises at V= 300 m/s while the engine produces an exhaust speed of Ve =700 m/s. The air mass flow rate is 200 kg/s and the fuel mass flow rate is 5 kg/s. Assume that the nozzle is perfectly expanded. ( na = 0.97, ne = 0.85, nb = 0.99, ni = 0.9, na = 0.98, a =6, QR = 44230 kj/kg, Ta = 300K) (a) Specific thrust (b) thrust-specific fuel consumption (TSFC) (c) compressor pressure ratio, Pa3/Po2 (d) turbine pressure ratio parameter, 0 (e) nozzle pressure ratio parameter, 0

Elements Of Electromagnetics
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Author:Sadiku, Matthew N. O.
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2. A turbojet-powered aircraft cruises at V = 300 m/s while the engine produces an exhaust
speed of Ve =700 m/s. The air mass flow rate is 200 kg/s and the fuel mass flow rate is 5
kg/s. Assume that the nozzle is perfectly expanded. ( na = 0.97, ne = 0.85, nb = 0.99,
ni = 0.9, na= 0.98, a =6, QR = 44230 kj/kg, Ta = 300K)
(a) Specific thrust
(b) thrust-specific fuel consumption (TSFC)
(c) compressor pressure ratio, Po3/Po2
(d) turbine pressure ratio parameter, 0
(e) nozzle pressure ratio parameter, 0n
Transcribed Image Text:2. A turbojet-powered aircraft cruises at V = 300 m/s while the engine produces an exhaust speed of Ve =700 m/s. The air mass flow rate is 200 kg/s and the fuel mass flow rate is 5 kg/s. Assume that the nozzle is perfectly expanded. ( na = 0.97, ne = 0.85, nb = 0.99, ni = 0.9, na= 0.98, a =6, QR = 44230 kj/kg, Ta = 300K) (a) Specific thrust (b) thrust-specific fuel consumption (TSFC) (c) compressor pressure ratio, Po3/Po2 (d) turbine pressure ratio parameter, 0 (e) nozzle pressure ratio parameter, 0n
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