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The lift coeffient, Cl, is a simply a rearangement of the lift equation, using different variables than the lift equation. The lift coefficient, Cl, is equal to the lift, L, divided by the quantity: density, ρ, times half the velocity, V, squared times the wing area, A. The lift coefficient is an effective way of comparing the performance of different airfoils and wings, even if they are different sizes, flying at different speeds, etc.