Response of a mach 6 cone-flare geometry to steady vortical disturbances: Effect of steady suction

Charles Hollender, Anubhav Dwivedi, Graham V. Candler

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations


A cone-flare at Mach 6 is prone to centrifugal instability (or Görtler instability) along its concave wall. We investigate perturbation amplification in the presence of random, upstream steady vortical disturbances using direct numerical simulations (DNS). Our calculations reveal that the flow field selectively amplifies perturbations resulting in periodic streamwise streaks with a given azimuthal wavelength. Amplification of these streaks causes significant base flow modifications, which can eventually lead to flow transition. We also investigate the effectiveness of distributed suction and its spatial location for attenuating the growth of these streaks. It is found that suction along the region of large curvature is more effective in controlling the growth of these perturbations, though satisfactory reduction in the growth is not observed in any of the suction locations considered.

Original languageEnglish (US)
Title of host publicationAIAA Aviation 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Number of pages14
ISBN (Print)9781624105890
StatePublished - 2019
EventAIAA Aviation 2019 Forum - Dallas, United States
Duration: Jun 17 2019Jun 21 2019

Publication series

NameAIAA Aviation 2019 Forum


ConferenceAIAA Aviation 2019 Forum
Country/TerritoryUnited States

Bibliographical note

Funding Information:
The authors would like to acknowledge the support of the Office of Naval Research, by grant numbers: N00014-16-1-2500 and N00014-19-1-2037. The views and conclusions expressed in this paper are those of the authors and should not be interpreting as representing those of the U.S. Government or other funding agencies. We would like to thank Drs. Ioannis Nompelis and Heath Johnson for their help with the paper.

Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.


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