Aerodynamic characteristics of flexible trailing edge adaptive wing by unstructured dynamic meshes

The aerodynamic characteristics of a flexible trailing edge adaptive wing are solved, where the NS equations are discretized with second order upwind scheme and dual time unstructured deforming meshes. The lift, drag and lift-to-drag ratio characteristics are calculated and compared with those of rigid wing with the same airfoil. It is found that the lift increases with the increasing trailing edge deflection linearly within linear lift ranges. Lift-to-drag ratio decreases with the increasing deflection angle. The lift characteristics of the flexible trailing edge adaptive wing are better than the corresponding rigid wing at middle to stall angle of attack, with moderate lift slope, and it offers more effective angle of attack.