I know that the lift equation for a single wing is L=Cl*0.5*A*r*V^2 where L is lift, Cl is the lift coefficient, A is the area, r is the air density, and V is velocity. Does this equation still apply to the elevator and rudder of a plane or is another equation used? If so, where can I find graphs of the lift coefficients of these parts?(adsbygoogle = window.adsbygoogle || []).push({});

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# Lift equation for elevator and rudder of a plane?

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