Lift Coefficient
In aerodynamics, the lift coefficient, abbreviated as \(C_l\), a dimensionless number, 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 foilbearing body such as a fixedwing aircraft.
Lift Coefficient formula 

\(\large{ C_l = \frac { 2 \; L } { \rho \; v^2 \; A } }\) (lift force)  
Symbol  English  Metric 
\(\large{ C_l }\) = lift coefficient  \(\large{ dimensionless }\)  
\(\large{ A }\) = area of surface  \(\large{ ft^2 }\)  \(\large{ m^2 }\) 
\(\large{ \rho }\) (Greek symbol rho) = density of fluid  \(\large{\frac{lbm}{ft^3}}\)  \(\large{\frac{kg}{m^3}}\) 
\(\large{ L }\) = lift force  \(\large{ lbf }\)  \(\large{N}\) 
\(\large{ v }\) = velocity  \(\large{\frac{ft}{sec}}\)  \(\large{\frac{m}{sec}}\) 
lift coefficient calculator
