Hello All....(adsbygoogle = window.adsbygoogle || []).push({});

I am just wondering about something.

The lift equation is,

[tex] L= \frac {C_L \rho A V^2} 2 [/tex]

where [tex] C_L= [/tex] coeficient of lift

[tex] \rho= [/tex] air density

[tex] A= [/tex] area of wingspan

[tex] V= [/tex] velocity of the aircraft

Does anyone have idea on what the typical coeficient of lift is? I know its calculated based on angle of attack and whatnot but does anyone know how this is done? any help greatly appreciated!

edit: fixed latex

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# Lift equation

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