In this article the results of numerical calculations and
experimental studies on wake vortex alleviation using
Differential Flap Setting (DFS) and Oscillating Flap
Setting (OFS) by means of a priciple model with
rectangular wing as a vortex generator should be
presented. The numerical part of the examination was
made as an Euler-computation provided with flow solver
TAU, the experiment was performed in water towing tank
at DLR Gottingen. The comparison of different
configurations according to flap setting, trigger frequency
and influence of HTP vortex was conducted in this paper.
Both numerical and experimental investigations have
shown that it is possible to affect the wake vortex
development using configurative methods on lift device.
Further investigations have to be done to calculate the
circulation and the rolling moment influence on following
aircrafts.