Lift Alleviation in Travelling Vortical Gusts

Yuanzhi Qian, Zhijin Wang, Ismet Gursul

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Lift alleviation by a mini-spoiler on airfoils, unswept and swept wings encountering an isolated counter-clockwise vortical gust was investigated by means of force and velocity measurements. The flow separation region behind the spoiler remains little affected during the gust encounter. The maximum lift reduction is found for the static stall angle of attack. The change in the maximum lift during the gust encounter is approximately equal to that in steady freestream. The comparison with plunging airfoils reveals that, for the same maximum gust and plunge velocity, the effectiveness of the mini-spoiler is much better in travelling gusts. This reveals the importance of the streamwise length scale of the incident gust. For the unswept wing, there is some three-dimensionality of the flow separation induced by the mini-spoiler near the wing-tip. The magnitude of the lift reduction can be estimated using the airfoil data and by making an aspect ratio correction for the reduced effective angle of attack. For the swept wing, the mini-spoiler can disrupt the formation of a leading-edge vortex induced by the incident vortex on the clean wing and can still reduce the maximum lift.
Original languageEnglish
Pages (from-to)1-22
JournalThe Aeronautical Journal
Issue number1316
Early online date30 Apr 2023
Publication statusPublished - 31 Oct 2023


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