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Unsteady effects in a hypersonic compression ramp flow with laminar separation

Published online by Cambridge University Press:  04 February 2021

Shibin Cao Open the ORCID record for Shibin Cao [Opens in a new window] ,
Jiaao Hao Open the ORCID record for Jiaao Hao [Opens in a new window] ,
Igor Klioutchnikov ,
Herbert Olivier  and
Chih-Yung Wen Open the ORCID record for Chih-Yung Wen [Opens in a new window]
Shibin Cao*
Affiliation:
Shock Wave Laboratory, RWTH Aachen University, 52056Aachen, Germany
Jiaao Hao
Affiliation:
Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong
Igor Klioutchnikov
Affiliation:
Shock Wave Laboratory, RWTH Aachen University, 52056Aachen, Germany
Herbert Olivier
Affiliation:
Shock Wave Laboratory, RWTH Aachen University, 52056Aachen, Germany
Chih-Yung Wen
Affiliation:
Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong Interdisciplinary Division of Aeronautical and Aviation Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong
*
†Email address for correspondence: cabinhit@outlook.com
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Abstract

Direct numerical simulations (DNS) are performed to investigate a hypersonic flow over a compression ramp with a free stream Mach number of 7.7 and a free stream Reynolds number of $4.2\times 10^{5}$ based on the flat plate length. The DNS results are validated by comparison with experimental data and theoretical predictions. It is shown that even in the absence of external disturbances, streamwise heat flux streaks form on the ramp surface downstream of reattachment, and that they are non-uniformly distributed in the spanwise direction. The surface heat flux exhibits a low-frequency unsteadiness, which propagates in the streamwise direction. Additionally, the unsteadiness of the heat flux streaks downstream of reattachment is coupled with a pulsation of the reattachment position. By conducting a dynamic mode decomposition (DMD) analysis, several oscillatory modes, characterised by streamwise low-frequency periodicity, are revealed in the separation bubble flow. The DNS results are further explained by a global stability analysis (GSA). Particularly, the flow structure of the leading DMD modes is consistent with that of the oscillatory unstable modes identified by the GSA. It is therefore concluded that the global instabilities are responsible for the unsteadiness of the considered compression ramp flow.

JFM classification

Boundary Layers: Boundary layer separation Compressible Flows: Shock waves
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 912 , 10 April 2021 , A3
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Copyright
© The Author(s), 2021. Published by Cambridge University Press

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References

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