The angle of attack at which an airfoil does not produce any lift. Its value is generally less than zero unless the airfoil is symmetric
- α0L: The zero-lift angle of attack. This is the angle of attack at which the aircraft’s wing generates zero lift. It’s an important parameter that affects the overall aerodynamic behavior of the aircraft.
- CLcr: The coefficient of lift at the critical point. The critical point is typically associated with the point at which the wing reaches its maximum coefficient of lift before stalling occurs. Stalling is a phenomenon where the airflow over the wing becomes separated, leading to a significant reduction in lift and potential loss of control.
- CLα: The coefficient of lift slope. This represents how the coefficient of lift changes with the angle of attack. It’s a measure of the wing’s efficiency in generating lift.