Design and testing of a low subsonic wind tunnel gust generator

Paul M.G.J. Lancelot*, Jurij Sodja, Noud P.M. Werter, Roeland De Breuker

*Corresponding author for this work

Research output: Contribution to journalArticleScientificpeer-review

21 Citations (Scopus)
54 Downloads (Pure)


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.

Original languageEnglish
Pages (from-to)125-144
Number of pages20
JournalAdvances in Aircraft and Spacecraft Science
Issue number2
Publication statusPublished - 1 Mar 2017


  • Computational fluid dynamics
  • Experimental aerodynamics
  • Experimental aeroelasticity
  • Fluid structure interaction
  • gust generator


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