The coefficient of lift (Cl) of an airfoil is a dimensionless parameter that quantifies the lift generated by the airfoil relative to the dynamic pressure and planform area. It is a crucial aerodynamic property used to characterize the performance of an airfoil and is determined by the angle of attack, airfoil geometry, and flow conditions. The equation is from Prandtl–Glauert Rule and Mach number should less than 0.7. The formula to calculate lift coefficient of an airfoil as follows:
Where:
- Cl0 is the incompressible lift coefficient (M=0),
- M is the Mach Number.