A review of the use of vortex generators for mitigating shock-induced separation
Author(s)
Titchener, Neil A.; Babinsky, Holger
Download193_2015_551_ReferencePDF.pdf (31.93Mb)
PUBLISHER_POLICY
Publisher Policy
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.
Terms of use
Metadata
Show full item recordAbstract
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.
Date issued
2015-02Department
Massachusetts Institute of Technology. Department of Aeronautics and AstronauticsJournal
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
ISSN
0938-1287
1432-2153