Flutter analysis of a morphing wing technology demonstrator : numerical simulation and wind tunnel testing

Koreanschi, A ORCID: https://orcid.org/0000-0002-7637-0783, Henia, MB, Guillemette, O, Michaud, F, Tondji, Y, Sugar-Gabor, O ORCID: https://orcid.org/0000-0001-6366-9623, Botez, RM and Flores salinas, M 2016, 'Flutter analysis of a morphing wing technology demonstrator : numerical simulation and wind tunnel testing' , INCAS Bulletin, 8 (1) , pp. 99-124.

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As part of a morphing wing technology project, the flutter analysis of two finite element models and the experimental results of a morphing wing demonstrator equipped with aileron are presented. The finite element models are representing a wing section situated at the tip of the wing; the first model corresponds to a traditional aluminium upper surface skin of constant thickness and the second model corresponds to a composite optimized upper surface skin for morphing capabilities. The two models were analyzed for flutter occurrence and effects on the aeroelastic behaviour of the wing were studied by replacing the aluminium upper surface skin of the wing with a specially developed composite version. The morphing wing model with composite upper surface was manufactured and fitted with three accelerometers to record the amplitudes and frequencies during tests at the subsonic wind tunnel facility at the National Research Council. The results presented showed that no aeroelastic phenomenon occurred at the speeds, angles of attack and aileron deflections studied in the wind tunnel and confirmed the prediction of the flutter analysis on the frequencies and modal displacements.

Item Type: Article
Schools: Schools > School of Computing, Science and Engineering > Salford Innovation Research Centre
Journal or Publication Title: INCAS Bulletin
Publisher: National Institute for Aerospace Research
ISSN: 2066-8201
Related URLs:
Depositing User: O Sugar-Gabor
Date Deposited: 10 Mar 2017 11:46
Last Modified: 15 Feb 2022 21:47
URI: https://usir.salford.ac.uk/id/eprint/41518

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