A review of the use of vortex generators for mitigating shock-induced separation
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193_2015_551_ReferencePDF.pdf
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31.94 MB
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Author(s)
Titchener, Neil A.
Babinsky, Holger
Date Issued
February 2015
Journal
Shock Waves
Publisher
Springer Berlin Heidelberg
Citation
Titchener, Neil, and Holger Babinsky. "A review of the use of vortex generators for mitigating shock-induced separation." Shock Waves 25:5 (2015), pp.473-494.
Version
Author's final manuscript
Abstract
This article reviews research into the potential of vortex generators to mitigate shock-induced separation. Studies ranging from those conducted in the early post-war era to those performed recently are discussed. On the basis of the investigations described in this report, it is clear that vortex generators can alleviate shock-induced boundary layer separation. Yet, it will be shown that their potential and efficiency varies considerably in practical applications. Much more success is reported in transonic test cases compared to separation induced in purely supersonic interactions. Under a variety of flow conditions, the best performance is achieved with vortex generators with a height of roughly half the boundary layer thickness and a shape similar to a swept vane. Notwithstanding this, vortex generator performance is not as consistent as it is in low-speed applications. Further work is required before vortex generators can be implemented into the design process for eliminating shock-induced separation on transonic wings and in supersonic inlets.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
Article is made available in accordance with the publisher's policy and may be subject to US copyright law. Please refer to the publisher's site for terms of use.
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DOI of Published Version
https://doi.org/10.1007/s00193-015-0551-x
