In flight mechanics and aerodynamics, the lift coefficient (CL) as a function of angle of attack (α) represents the relationship between the lift generated by an airfoil or an aircraft’s wing and the angle at which the airfoil or wing is inclined to the oncoming airflow.
- CLα: The lift coefficient as a function of angle of attack (α).
- A: Aspect ratio
- Clα: The lift coefficient at a reference angle of attack.