|
A cambered aerofoil generates no lift when it is moving parallel to an axis called the zero lift axis (or the zero lift line.) When the angle of attack on an aerofoil is measured relative to the zero lift axis it is true to say the lift coefficient is zero when the angle of attack is zero.〔Anderson, John D. Jr, ''Introduction to Flight'', Section7.4 (fifth edition)〕 For this reason, on a cambered aerofoil the zero lift line is better than the chord line when describing the angle of attack.〔''Such a line is called the line of zero lift or neutral lift line, and would in some senses be a better definition of the chord line, but it can only be found by wind tunnel experiments for each aerofoil, and, even when it has been found, it is awkward from the point of view of practical measurements.'' Kermode, A.C., ''Mechanics of Flight'', (p.76, eighth edition)〕 When symmetric aerofoils are moving parallel to the chord line of the aerofoil, zero lift is generated. However, when cambered aerofoils are moving parallel to the chord line, lift is generated. (See diagram at right.) For symmetric aerofoils, the chord line and the zero lift line are the same.〔Clancy, L.J., ''Aerodynamics'', paragraph 5.7(a)〕 == See also == * Angle of attack * Aerobatics * Aerobatic maneuver 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「Zero lift axis」の詳細全文を読む スポンサード リンク
|