Aircraft Wake Vortex Alleviation: An Experimental Approach

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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.

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