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Transitional shock-wave/boundary-layer interactions in hypersonic flow

Sandham, Neil and Schülein, Erich and Wagner, Alexander and Willems, Sebastian and Steelant, Johan (2014) Transitional shock-wave/boundary-layer interactions in hypersonic flow. Journal of Fluid Mechanics, 752 (6), pp. 349-382. Cambridge University Press. doi: 10.1017/jfm.2014.333. ISSN 0022-1120.

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Official URL: http://journals.cambridge.org/download.php?file=%2FFLM%2FFLM752%2FS0022112014003334a.pdf&code=bf958ad19ce9f834d36eebf438633b36


Strong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG). The experimental measurements include shadowgraph and infrared thermography as well as heat transfer and pressure sensors. Direct numerical simulations (DNS) are carried out to compare with selected experimental flow conditions. The combined approach allows an assessment of the effects of unit Reynolds number, disturbance amplitude, shock impingement location and wall cooling. Measures of intermittency are proposed based on wall heat flux, allowing the peak Stanton number in the reattachment regime to be mapped over a range of intermittency states of the approaching boundary layer, with higher overshoots found for transitional interactions compared with fully turbulent interactions. The transition process is found to develop from second (Mack) mode instabilities superimposed on streamwise streaks.

Item URL in elib:https://elib.dlr.de/89769/
Document Type:Article
Title:Transitional shock-wave/boundary-layer interactions in hypersonic flow
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Willems, SebastianUNSPECIFIEDhttps://orcid.org/0000-0002-5576-7829UNSPECIFIED
Journal or Publication Title:Journal of Fluid Mechanics
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
Page Range:pp. 349-382
Publisher:Cambridge University Press
Keywords:high-speed flow, shock waves, transition to turbulence
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Flight Physics (old)
Location: Göttingen , Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > High Speed Configurations
Institute of Aerodynamics and Flow Technology > Spacecraft
Institute of Aerodynamics and Flow Technology > Über- und Hyperschalltechnologien
Deposited By: Micknaus, Ilka
Deposited On:18 Jul 2014 10:20
Last Modified:21 Sep 2023 12:45

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