The lift coefficient slope (CLα) for a wing with a certain aspect ratio in flight mechanics refers to how the lift coefficient (CL) changes with changes in the angle of attack (α). In other words, it quantifies the rate of change of lift produced by the wing as the angle of attack changes.
- CLα: Lift coefficient slope for the wing with a certain aspect ratio (A).
- A: Aspect ratio of the wing.
- Clα: Lift coefficient slope for the reference wing (usually a wing with aspect ratio of 2).