The “Coefficient of Lift” (CL) is a dimensionless parameter that represents the lift force generated by an airfoil or wing relative to the dynamic pressure of the airflow.
The coefficient of lift is defined as the ratio of the lift force (L) acting on the airfoil or wing to the dynamic pressure (q) and the reference area (S) of the airfoil
2 * L / (ρ * S * V^2)
- CL: Coefficient of Lift
- L: Lift force acting on the airfoil or wing
- ρ: Air density
- S: Reference area of the airfoil (the planform area perpendicular to the airflow)
- V: Airspeed of the aircraft