Wake vortex alleviation by differential and oscillating flap settings: A numerical and experimental study

In this article the results of numerical simulations and experimental investigations on wake vortex alleviation using Differential Flap Setting (DFS) and Oscillating Flap Setting (OFS) by means of a principle model with rectangular wing as a vortex generator are presented. The numerical investigations was made using Euler computations with the DLR flow solver TAU, the experiment was performed in a water towing tank at DLR Goettingen. The comparison of different configurations according to flap setting, trigger frequency and influence of Horizontal Tail Plane (HTP) vortex is conducted in this paper. Both the numerical and experimental investigations show that it is possible to influence the wake vortex development using configurative applicatins on aircraft wings.