The lift coefficient (CL) is a mathematical parameter used by aerodynamicists to quantify the lifting capabilities of a specific airfoil or entire aircraft at a given angle of attack. It accounts for the complex dependencies of shape, inclination, and air properties. Engineers use the CL value in the lift equation to determine how much wing area is needed to keep an aircraft airborne at specific speeds and altitudes.
If we drop the flaps to fifteen degrees, the CL increases enough to lower our stall speed by ten knots.
Also heard as
- lift coefficient
- coefficient of lift
Related terms
Angle of attack
The acute angle between the chord line of an airfoil and the oncoming relative wind.
Centre of lift
The theoretical point on an airframe where the sum total of all aerodynamic lifting forces acts.
Flap
A hinged surface on the trailing edge of an aircraft wing used to increase lift and drag.