The lift coefficient (Cl) for an airfoil section located at an arbitrary spanwise station represents the dimensionless measure of the lift generated by that specific section of the airfoil. It quantifies the relationship between the lift force produced by the airfoil section and the dynamic pressure of the incoming airflow.
- Cl: Lift coefficient for the thin airfoil section.
- αeff(y₀): Effective angle of attack at the spanwise station y₀.
- αL=0: Zero-lift angle of attack.