Influence of Differential Spoiler Settings on the Wake Vortex Characterization and Alleviation

摘要

Experimental investigations using particle image velocimetry technique have been carried out for the evaluation ofnthe differential spoiler setting capabilities in modifying the spanwise wing load and further reduce the wake vortexnhazard. The aircraft half model (at high lift configuration) was investigated for two differential spoiler settings.nResults reveal a noticeable inboard shift of spanwise wing loading. Implementation of a differential spoiler settingnresults in a substantial redistribution of the flap tip vortex circulation with an increase in the diameter of themergednvortex by a factor of up to 2.72 relative to the undisturbed flap tip vortex. Inspection of the cross-streamdistributionnof axial vorticity shows a reduction by a factor of up to 2.33 in the peak vorticity value. A 44% decrease of thenmaximumcrossflowvelocity relative to the undisturbed flap tip vortex crossflowvelocitywas recorded for the case ofndeployed spoilers. Finally assessment of the differential spoiler setting capabilities as a wake vortex attenuationndevice reveals that, while position of themaximuminduced rollingmoments in the flap tip area is little influenced bynthe differential spoiler setting, the maximum induced rolling moment coefficient was reduced to nearly one third ofnthe undisturbed flap tip vortex value.