Testing of Folding Wing-Tip for Gust Load Alleviation in High Aspect Ratio Wing

Research output: Chapter in Book/Report/Conference proceedingConference Contribution (Conference Proceeding)

6 Citations (Scopus)
172 Downloads (Pure)

Abstract

Folding wing-tips have begun to feature on recent aircraft designs, as a solution for compliance with existing airport gate width, whilst the higher aspect ratio will lead to lower induced drag and better overall fuel efficiency. Recent studies have suggested that by allowing folding of the wing-tip during flight, additional gust load alleviation can be achieved. This paper describes the follow-on work from a previous experimental study, in which the folding wing-tip concept is now applied to a new wind tunnel model of a high aspect ratio wing with a much-reduced bending stiffness. Using a low-speed wind tunnel with a vertical gust generator, the experiment examined the load alleviation performance through a range of one-minus-cosine gust inputs and found up to 11% reduction in peak wing-root bending moment. In addition, a movable secondary aerodynamic surface was fitted to the folding wing-tip which demonstrated that such a device was able to control the orientation of the folding wing-tip effectively in steady aerodynamic conditions, as well as achieving further reduction in peak wing-root bending moment during gust encounters through active control.
Original languageEnglish
Title of host publicationAIAA Scitech 2019 Forum
Pages1-15
Number of pages15
ISBN (Electronic)978-1-62410-578-4
DOIs
Publication statusPublished - 6 Jan 2019
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: 7 Jan 201911 Jan 2019
https://scitech.aiaa.org/

Conference

ConferenceAIAA Scitech Forum, 2019
CountryUnited States
CitySan Diego
Period7/01/1911/01/19
Internet address

Bibliographical note

acceptance date is provisional, based on the publication information

Keywords

  • Folding wing-tip
  • aeroelasticity
  • Semi-elastic hinge

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