The lift coefficient during cruise in flight mechanics refers to the value of the coefficient of lift (CL) that an aircraft sustains while flying in its normal, non-manoeuvring, and level flight condition. Cruise flight is typically associated with steady flight at a constant velocity and altitude, where the lift generated by the aircraft’s wings is balanced with the weight of the aircraft
CLcr = CLα * (αcr - α0L)
- CLcr: The coefficient of lift at the critical point. The critical point is typically associated with the angle of attack 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 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.
- αcr: The critical angle of attack. This is the angle of attack at which the wing reaches its maximum coefficient of lift before stalling occurs.
- α0L: The zero-lift angle of attack. This is the angle of attack at which the wing generates zero lift.