the force of lift excerted on an airplane is defined as(adsbygoogle = window.adsbygoogle || []).push({});

F = Lc * D * v^2 * A

where Lc is the lift coefficient, D is the air density, v velocity, and A the lift area of the wing structure. If i use SI units, the Force is expressed in Newtons.

What i'm trying to grasp here, is how does this apply in practicality?

If i use the numbers Lc = 1.0, D = 1.225, v = 100, A = 21, (not random values) the result is 257,250 N ... now ... what does that MEAN? that the wings on that airplane produces enough lift to accelerate a 2000 kg airframe upwards at 128.6 m/s^2 ? Or, am i not calculating in gravitation? should the correct formula be 257250 / (2000 * 9.8) = 13.1 m/s^2 ? That just seems like an awfully high number... Or is it impossible to determine accurate lift unless you account for drag?

Thanks for any help

-- Pops

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# Airplane lift

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