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Aeroacoustic mechanisms explain universal behaviour in high-Mach number cylinder wakes

Published online by Cambridge University Press:  29 April 2025

Premika S. Thasu Open the ORCID record for Premika S. Thasu [Opens in a new window] ,
Gaurav Kumar  and
Subrahmanyam Duvvuri Open the ORCID record for Subrahmanyam Duvvuri [Opens in a new window]
Premika S. Thasu
Affiliation:
Turbulent Shear Flow Physics and Engineering Laboratory, Department of Aerospace Engineering, Indian Institute of Science, Bengaluru 560012, India
Gaurav Kumar
Affiliation:
Turbulent Shear Flow Physics and Engineering Laboratory, Department of Aerospace Engineering, Indian Institute of Science, Bengaluru 560012, India
Subrahmanyam Duvvuri*
Affiliation:
Turbulent Shear Flow Physics and Engineering Laboratory, Department of Aerospace Engineering, Indian Institute of Science, Bengaluru 560012, India
*
Corresponding author: Subrahmanyam Duvvuri, [email protected]
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Abstract

Recent experimental studies reveal that the near-wake region of a circular cylinder at hypersonic Mach numbers exhibits self-sustained flow oscillations. The oscillation frequency was found to have a universal behaviour. These oscillations are of a fundamentally different nature in comparison with flow oscillations caused due to vortex shedding, which are commonly observed in cylinder wakes at low-subsonic Mach numbers. The experimental observations suggest an aeroacoustic feedback loop to be the driving mechanism of the oscillations at high Mach numbers. An analytical aeroacoustic model that successfully predicts the experimentally observed frequencies and explains the universal behaviour is presented here. The model provides physical insights into and informs us of flow regimes where deviations from universal behaviour are to be expected. These findings hold relevance for a wider class of non-canonical wake flows at high Mach numbers.

JFM classification

Acoustics: Aeroacoustics Aerodynamics: High-speed flow Wakes/Jets: Wakes
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 1010 , 10 May 2025 , A6
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Copyright
© The Author(s), 2025. Published by Cambridge University Press

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Footnotes

†

Presently at Case Western Reserve University, USA.

‡

Presently at A-STAR Institute of High Performance Computing, Republic of Singapore.

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