Airfoil Section Lift Coefficient Calculator

The lift coefficient (CL​) for an airfoil section is a critical parameter in aircraft design, representing the effectiveness of the airfoil in generating lift

• CL section​​ is the lift coefficient for the airfoil section.
• $\alpha$ is the angle of attack
• αL0​​ is the zero-lift angle of attack.
• $2\pi$ represents the lift-curve slope