In flight mechanics and aerodynamics, the change in lift coefficient (CL) per unit change in angle of attack (α) is a crucial parameter known as the “lift curve slope,” often denoted as CLα. This parameter describes how much lift an aircraft’s wing generates as the angle of attack is increased or decreased.
- CLα: This represents the change in lift coefficient (CL) per unit change in angle of attack (α). It’s often referred to as the “lift curve slope” and indicates how much lift the aircraft generates as the angle of attack is increased.
- A: This typically represents the aspect ratio of the aircraft’s wings. The aspect ratio is a measure of how long and narrow the wings are, and it influences the efficiency and behavior of the wings.
- Clα,in: This is the lift curve slope of the aircraft’s wing in an idealized, incompressible flow. It represents the change in lift coefficient per unit change in angle of attack when various complexities like compressibility effects are ignored.