In flight mechanics, the maximum lift coefficient, often denoted as (CLmax), represents the peak value of the lift coefficient that an aircraft’s wings can achieve before experiencing an aerodynamic stall. This coefficient characterizes the maximum lift generated by the wings for a given angle of attack. A higher allows the aircraft to achieve liftoff at a lower speed, enhancing takeoff performance. The formula to calculate Maximum lift Coefficient as follows:
Where:
- W is the weight in N.
- ρ∞ is the density in kg/m3.
- S is the Wing area in m2.
- Vstall is the Stall velocity in m/s.
- CLmax is the Maximum Lift coefficient.