coefficient of lift
Also found in: Acronyms, Wikipedia.
coefficient of lift (CL)
A form in which aerodynamic data is presented. A lift coefficient is dependent upon the angle of attack, shape of the wing section and plan form, condition of the wing surface, Mach number, and Reynolds number. Since most other factors are constant, CL values are plotted against the angle of attack. The value of CL rises up to the stalling angle, where it falls off rapidly. Lift coefficient (CL) = Lift (L)/Dynamic Pressure (q) × Wing Area (S) or CL = L/qS, or 2L/ρ V2S.