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zero-lift angle<br />
The angle of attack at which an airfoil does not produce any lift. Its value is generally less than zero unless<br />
the airfoil is symmetrical.<br />
This from Foundations of aerodynamics, 5 th ed. By Chow and Kuethe<br />
http://www.answers.com/topic/zero-lift-angle<br />
These are from text :foundation of aerodynamics by Kuethe and Chow<br />
1. the center of pressure is at ¼ chord for all values of lift coeff.<br />
2. center of pressure (c.p.) of a force is defined as the point about which the moment vanishes.<br />
3. The geometric angle of attack is defined as the angle between the flight path and the chord line of the airfoil.<br />
When the geometric angle of attack is zero, the lift coeff. Is zero.<br />
4. The point about which the moment coeff. Is independent of the angle of attack is called the aerodynamic<br />
center of the section. (a.c.)<br />
5. a.c. is at the ¼ chord line point.<br />
6. The value of the angle of attack that makes the lift coeff. Zero is called the angle of zero lift (Z.L.L.)<br />
There are from Foundations<br />
of aerodynamics, 5 th ed. By<br />
Chow and Kuethe<br />
19.5 Some strange shaped airplanes<br />
Image http://edition.cnn.com/2014/01/16/travel/inside-airbus-beluga/index.html?hpt=ibu_c2<br />
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