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| {{Refimprove|date=January 2008}}
| | Hi there, I am Alyson Boon although it is not the title on my beginning certificate. I am truly fond of to go to karaoke but I've been taking on new things lately. Office supervising is where her main earnings comes from. Her family members life in Ohio.<br><br>Also visit my site :: live psychic reading ([http://www.octionx.sinfauganda.co.ug/node/22469 click through the following internet site]) |
| {{expert-subject|Aviation|ex2=Engineering|date=February 2009}}
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| In [[fixed-wing aircraft]] driven by one or more jet engines, the '''performance''' of the jet engine is important to the operation of the aircraft and includes measurement of [[thrust]], [[fuel consumption]], [[Noise pollution|noise]] and [[Emission standard|engine emissions]].
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| The thrust, noise and emission elements of the performance of a jet engine are of vital importance in the [[takeoff]] phase of operation of the aircraft. The thrust and fuel consumption elements, and their variation with [[Altitude#Altitude in aviation|altitude]] and [[airspeed]], are of vital importance in the [[climb]] and [[Cruise (flight)|cruise]] phases of operation of the aircraft.
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| ==Thrust==
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| {{main|Turbojet#Net thrust}}
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| The thrust from a jet engine is determined by the velocity of exhaust gases measured relative to the engine.
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| The velocity of the exhaust gas as it leaves a jet engine is <math>V_j\;</math>:<ref name=FCT918>G. Van Wylen and R. Sonntag, ''Fundamentals of Classical Thermodynamics'', Section 9.18</ref>
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| :<math>V_j^2=2(h_4-h_5)</math><br />
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| where
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| :{| border="0" | |
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| | <math>h_4\;</math> || is the specific [[enthalpy]] of the gas leaving the turbine and entering the [[propelling nozzle]]
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| | <math>h_5\;</math> || is the specific enthalpy of the gas after it has left the propelling nozzle
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| |}
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| Alternatively, <math>V_j\;</math> is related to the temperatures of the exhaust gas:<ref name=FCT918/>
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| :<math>V_j^2=2 C_{p0} (T_4-T_5)</math><br /> | |
| where
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| :{| border="0" | |
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| | <math>C_{p0}\;</math> || is the [[specific heat]] of exhaust gas at constant pressure
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| |-
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| |<math>T_4\;</math> || is the temperature of the gas leaving the turbine and entering the propelling nozzle
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| |-
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| | <math>T_5\;</math> || is the temperature of the gas after it has left the propelling nozzle
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| |}
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| ==Notes==
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| {{Reflist}}
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| ==References==
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| * Kerrebrock, Jack L. (1992), ''Aircraft Engines and Gas Turbines'', The MIT Press, Cambridge, Massachusetts USA. ISBN 0-262-11162-4
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| * G. Van Wylen and R. Sonntag (1985), ''Fundamentals of Classical Thermodynamics'', 3rd edition, John Wiley & Sons, New York NY ISBN 04718293311 {{Please check ISBN|reason=Invalid length.}}
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| [[Category:Jet engines]]
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