Mechanical simulation and aerodynamic analysis on a new type of wing trailing edge variable camber

By using computational fluid dynamics and CATIA DMU Kinematics, a high-lift system that could be used on the present and future civil aircraft for varying wing camber during cruise has been studied. It consists of flap mechanism and drooping spoiler. Kinematic analysis of the flap mechanism shows that there won't be any gap on the wing surface during cruise. Besides, the track of flap meets the requirements of takeoff and landing. Compared with the simple hinged flap, the linear range of lift coefficient of takeoff configurations that applied the flap mechanism increases by 0.05, and the corresponding increase of lift to drag ratio is from 3% to 0.2%. The maximum lift coefficient of landing configuration with drooping spoiler increases by 1.14% and the linear range of lift coefficient increases to 0.15 than the configuration without spoiler droop, which demonstrates its high efficiency. The flap mechanism has been used to change trailing edge camber on the basis of 2D cruise foils and the lift to drag ratio has been improved. The drag-divergence Mach number increases with trailing edge deflection angle. The flap mechanism has also been used to change trailing edge camber of a long-range, wide-body transport aircraft. In the entire range of lift coefficient available during cruise, the L/D of initial configuration has increased by 0.345%~2.28%. In conclusion, the high-lift system used for varying camber during cruise shows great benefits on aerodynamics without increasing complexity and weight of mechanism.