# Lift Coefficient

In aerodynamics, the lift coefficient, abbreviated as \(C_l\), is a dimensionless number that represents the lift generated by a lifting body to the fluid density around the body, the density of the fluid around the body, velocity of the fulid and an associated reference area. The lifting body can be a foil or a complete foil-bearing body such as a fixed-wing aircraft.

\(\large{ C_l = \frac { 2 \; L } { \rho \; v^2 \; A } }\) Where: \(\large{ C_l }\) = lift coefficient \(\large{ A }\) = area of the surface \(\large{ \rho }\) (Greek symbol rho) = density of the fluid \(\large{ L }\) = lift force \(\large{ v }\) = velocity |