Design and testing of a low subsonic wind tunnel gust generator

Journal article (2017)

Authors

P.M.G.J. Lancelot Aerospace Structures & Computational Mechanics - Aerospace Engineering
J. Sodja Aerospace Structures & Computational Mechanics - Aerospace Engineering
N.P.M. Werter Aerospace Structures & Computational Mechanics - Aerospace Engineering
R. De Breuker Aerospace Structures & Computational Mechanics - Aerospace Engineering
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Copyright: © 2017 P.M.G.J. Lancelot, J. Sodja, N.P.M. Werter, R. De Breuker
DOI
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https://doi.org/10.12989/aas.2017.4.2.125
Fluid structure interaction Computational fluid dynamics Experimental aerodynamics Experimental aeroelasticity Gust generator
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Published Date

01-03-2017

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

This paper summarises the design of a gust generator and the comparison between high fidelity numerical results and experimental results. The gust generator has been designed for a low subsonic wind tunnel in order to perform gust response experiments on wings and assess load alleviation. Special attention has been given to the different design parameters that influence the shape of the gust velocity profile by means of CFD simulations. Design parameters include frequency of actuation, flow speed, maximum deflection, chord length and gust vane spacing. The numerical results are compared to experimental results obtained using a hot-wire anemometer and flow visualisation by means of a tuft and smoke. The first assessment of the performance of the gust generator showed proper operation of the gust generator across the entire range of interest.