Aircraft Wake Vortex Alleviation

Motivation behind the present investigation is the alleviation of the rolling moment induced on the following aircraft by means of a DSS's. Particle image velocimetry was used to characterize wing tip vortex structures as well as quantifying vortex meandering. DSS capabilities in modifying the span-wise wing load and further reduces the wake vortex hazard were carried out. PIV technique was used to measure the wake velocities down-stream of the aircraft half model. Results reveal a noticeable inboard shift of wing loading along with the direct interaction of the spoiler's wake and flap tip vortex for the inboard loading cases. Implementation of DSS results in a substantial redistribution of the flap tip vortex circulation. A 44% decrease of the maximum cross-flow velocity was recorded for the case of deployed spoilers. Evaluations of the outboard loading results indicate a limited diffusion experienced by the vortex due to the increased level of turbulence. DSS's capabilities as a wake vortex attenuation device reveals, while position of the maximum induced rolling moments is little influenced by the DSS's, the maximum induced rolling moment coefficient was reduced to one third.