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Specific thrust : ウィキペディア英語版 | Specific thrust
Specific thrust is a term used in gas turbine engineering to show the relative bulk of a jet engine (e.g. turbojet, turbofan, etc.) and is defined as the ratio: net thrust/total intake airflow. ==Low specific thrust engines==
A modern civil turbofan has a low specific thrust (~30 lbf/(lb/s)) to keep the jet noise at an acceptable level, and to achieve low fuel consumption, because a low specific thrust helps to improve specific fuel consumption (SFC). This low specific thrust is usually achieved with a high bypass ratio. Additionally a low specific thrust implies that the engine is relatively large in diameter, for the net thrust it produces. Consequently such aircraft engines are normally located externally, in a separate nacelle or pod, attached to the wing, or the rear fuselage.
抄文引用元・出典: フリー百科事典『 ウィキペディア(Wikipedia)』 ■ウィキペディアで「Specific thrust」の詳細全文を読む
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