Talk:Angle of attack

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This would make a lot more sense if somebody could say what u, v and w are, and Vt GRAHAMUK

Formulas clipped from main:

$\alpha\ = \tan^{-1}\ \left ( \frac{w}{u} \right )$

Where $Vt = \sqrt{u^2 + v^2 + w^2}$

The diagram says it all. Meggar 03:22, 2005 August 7 (UTC)

Well, not really. The diagram doesn't include u, w or v, nor Vt. However, you're right in the sense that the diagram is all you need, not really sure what the formulae are meant to add to the article. However, if they stay, they need fully explaining. Graham 08:23, 7 August 2005 (UTC)

[edit] defining the formula terms....

alpha = angle of attack

Vt = total aircraft velocity (magnitude of velocity vector of the aircraft)

u,v,w are the components of the aircraft's velocity that make up the Vt vector.

u is the velocity of the aircraft along its longitudinal axis, also known as the intertial x-axis, which runs from tail to nose in the positive direction

v is the velocity of the aircraft along its lateral axis, also known as the intertial y-axis, which runs from left wing to right wing in the positive direction

w is the velocity of the aircraft along its vertical axis, also known as the intertial z-axis, which runs from top of aircraft to belly in the positive direction

this axis system is fixed (intertial) to the aircraft, and its origin is usually near the aircraft's center of gravity

furthermore, the sideslip angle, greek letter Beta, may be calculated from.... beta = asin (v/Vt) but this probably deserves its own wiki page

cheers

Now that the terms are defined: The first formula gives alpha as already shown in the diagram but in rectangular coordinates. The second gives total velocity that has no place in this article at all. Maybe they will fit into some other future page that lays out the whole system. Meggar 21:04, 2005 August 12 (UTC)

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Talk:Angle of attack

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[edit] defining the formula terms....

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