In flight mechanics, the lift coefficient (Cl) is a dimensionless parameter that plays a fundamental role in aerodynamics and the analysis of aircraft performance. It is a key concept used to describe the lift generated by an airfoil (such as a wing) or an entire aircraft. The lift coefficient is defined as the ratio of the lift force (L) acting on the aircraft to the dynamic pressure (q) and the reference area (S) of the airfoil or wing
CL = w / (0.5 * ρ * v^2 * S)
where: CL = Lift coefficient W=weight ρ = Air density v = Airspeed of the aircraft S = Reference area of the wing (wing area)