`L = C_L * 1/2 *rho *V^2 *S`

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Lift opposes the downward force of weight, is produced by the dynamic effect of the air acting on the wing, and acts perpendicular to the flightpath through the wing’s center of lift.

In steady flight, the sum of these opposing forces is equal to zero. There can be no unbalanced forces in steady, straight flight (Newton’s Third Law)

Lift Force can therefore be expressed as:-

L = C_L*1/2* ρ *V^2 *S

Where:-

L = Lift Force

C_L = The lift Coefficient

V = The speed of airplane relative to the air (m/s)

S = The wing Surface (m^2)

ρ = The air density.