The lift coefficient (Cl) is a dimensionless aerodynamic parameter used to characterize the lift generation of an airfoil or wing. It quantifies the relationship between the lift force generated by the wing or airfoil and various factors like its geometry, angle of attack, and airspeed.Formula:
The lift coefficient is typically calculated using the following formula:
- L is the lift coefficient (dimensionless)
- L is the lift force (in newtons, N)
- ρ (rho) is the air density (in kilograms per cubic meter, kg/m³)
- V is the velocity of the airfoil or wing (in meters per second, m/s)
- A is the reference area of the wing or airfoil (in square meters, m²)