Analyzing the Dynamic Behavior of a High Aspect Ratio Wing Incorporating a Folding Wingtip

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Abstract

High aspect ratio wings have been the focus of recent aircraft designs for improving fuel efficiency through induced drag reduction. The lengthened wingspan derived from these designs have led to the introduction of folding wingtips in order to meet airport gate width requirements. Previous numerical and experimental studies have demonstrated that folding wingtips can also provide a gust load alleviation benefit, when the folding wingtips are able to rotate freely about the hinge during the gust encounter. This work examines the dynamic characteristics and behavior of the folding wingtip, and the overall wing in such a configuration. A series of wind tunnel tests was conducted using a specially designed high aspect ratio wing model to establish its modal characteristics through application of a stepped-sine frequency sweep, performed using a gust generator as well as a secondary aerodynamic surface incorporated into the wingtip as the excitation source. In addition, a pseudo-random gust sequence was used as a faster test method through broadband excitation, which yielded results that were in excellent agreement with the stepped-sine methods.
Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Pages1-12
Number of pages12
ISBN (Electronic)978-1-62410-595-1
DOIs
Publication statusPublished - 5 Jan 2020
EventAIAA SciTech Forum - Hyatt Regency Hotel, Orlando, United States
Duration: 6 Jan 202010 Jan 2020

Conference

ConferenceAIAA SciTech Forum
CountryUnited States
CityOrlando
Period6/01/2010/01/20

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  • Cite this

    Cheung, R. C. M., Rezgui, D., Cooper, J. E., & Wilson, T. (2020). Analyzing the Dynamic Behavior of a High Aspect Ratio Wing Incorporating a Folding Wingtip. In AIAA Scitech 2020 Forum (pp. 1-12). [AIAA 2020-2290] American Institute of Aeronautics and Astronautics Inc. (AIAA). https://doi.org/10.2514/6.2020-2290