On the Structure and Attenuation of an Aircraft Wake

Abstract

The results of an experimental investigation of the wake-vortex structure behind a swept and tapered wing with slats and e aps arepresented. The wind-tunnel test is part of a project funded by the German Research Association to investigate the e ow structure of wings with different e ap extensions. The investigation aims at studying the characteristics of lift-generated vortices in order to e nd ways to attenuate dangerous wake vortex encounters for following aircraft during takeoff and landing such that an increase in airport capacity can be achieved. The wake structureismeasuredfordifferente ap settingsbymeansofhot-wireanemometry atdifferent streamwisepositions in the near e eld behind the wing. The measured data are evaluated to examine vortex parameters such as core radius, maximum tangential velocities, circulation distributions, turbulence levels, and maximum induced rolling moments on a following aircraft. In addition, for one e ap setting means of alleviation with a wing e n at different angles of incidence mounted at the outboard e ap edge region are examined. The e n causes a large increase of the vortex core and a reduction of the maximum induced rolling moment within the measured region.