Hypersonic oscillating shock-wave/boundary-layer interaction on a flat plate

Currao, Gaetano M. D. and McQuellin, Liam P. and Neely, Andrew J. and Gai, Sudhir L. and O'Byrne, Sean and Zander, Fabian ORCID: https://orcid.org/0000-0003-0597-9556 and Buttsworth, David R. and McNamara, Jack J. and Jahn, Ingo ORCID: https://orcid.org/0000-0001-6962-8187 (2021) Hypersonic oscillating shock-wave/boundary-layer interaction on a flat plate. AIAA Journal: devoted to aerospace research and development, 59 (3). pp. 940-959. ISSN 0001-1452


This work discusses the design, measurement, and simulation of an oscillating shock-wave/boundary-layer interaction on a flat plate at Mach 5.8 and Re ∞ =7×10 6   m −1 Re∞=7×106  m−1. The shock generator is free to pitch and oscillates with a frequency of 42 Hz, resulting in a shock that varies in intensity and impingement point, with a maximum flow-deflection angle of approximately 10 deg. Transition appears to take place downstream of the separated region for both static (with a fixed flow-deflection angle) and dynamic experiments; however, heat-flux values are typically between laminar and turbulent solutions, thus suggesting that a complete transition to a fully turbulent boundary layer is delayed because of the favorable pressure gradient induced by the impinging expansion wave originating from trailing edge of the shock generator. Peak pressure is typically overpredicted by laminar simulations for large deflection angles. Starting from the reattachment point, heat-flux measurements show that the boundary layer gradually deviates from the laminar solution towards a fully turbulent boundary layer. Vortices are observed in the reattachment region, and their distribution is solely a function of the boundary-layer properties at the separation point. Transient effects induced by the shock motion result in a maximum bubble length variation of 30%. For the static cases, the separated region amplified disturbances with a frequency of approximately 200 Hz. In the dynamic experiment, harmonics induced by the pseudosinusoidal motion of the shock generator were measured everywhere on the plate.

Statistics for USQ ePrint 43926
Statistics for this ePrint Item
Item Type: Article (Commonwealth Reporting Category C)
Refereed: Yes
Item Status: Live Archive
Additional Information: Files associated with this item cannot be displayed due to copyright restrictions.
Faculty/School / Institute/Centre: Historic - Faculty of Health, Engineering and Sciences - School of Mechanical and Electrical Engineering (1 Jul 2013 - 31 Dec 2021)
Faculty/School / Institute/Centre: Current - Institute for Advanced Engineering and Space Sciences (1 Aug 2018 -)
Date Deposited: 26 Oct 2021 02:47
Last Modified: 09 Sep 2022 02:54
Fields of Research (2008): 09 Engineering > 0901 Aerospace Engineering > 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Fields of Research (2020): 40 ENGINEERING > 4001 Aerospace engineering > 400106 Hypersonic propulsion and hypersonic aerothermodynamics
Identification Number or DOI: https://doi.org/10.2514/1.J059590
URI: http://eprints.usq.edu.au/id/eprint/43926

Actions (login required)

View Item Archive Repository Staff Only