The coefficient of lift (cl) for a two-dimensional body, such as an airfoil, is a dimensionless parameter used to describe the lift generated by the body in a fluid flow. It represents the lift force per unit span of the body, normalized by the dynamic pressure of the incoming flow and a reference area.
- cl is the lift coefficient.
- L’ is the lift force acting on the body.
- q ∞ is the freestream dynamic pressure of the fluid flow.
- c is the wing area for two-dimensional body.