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Time-Resolved Visualization of Instability Waves in a Hypersonic Boundary Layer

Laurence, Stuart and Wagner, Alexander and Hannemann, Klaus and Wartemann, Viola and Lüdeke, Heinrich and Tanno, Hideyuki and Itoh, Katsuhiro (2012) Time-Resolved Visualization of Instability Waves in a Hypersonic Boundary Layer. AIAA Journal, 50 (1), pp. 243-246. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.J051112. ISSN 0001-1452.


Official URL: http://www.aiaa.org/noBookmark/


LAMINAR-TURBULENT transition in hypersonic boundary layers remains a challenging subject. This is especially true of the hypervelocity regime, in which an intriguing phenomenon is the possible damping of second-mode disturbances by chemical and vibrational nonequilibrium processes. To generate flows with sufficiently high enthalpy to investigate such effects, the use of shock-tunnel facilities is necessary; furthermore, it is now generally accepted that direct measurements of the instability mechanisms active within the boundary layer, together with a characterization of the freestream disturbance environment, are required, as simple measurements of transition locations can lead to ambiguous conclusions. However, as difficult as the accurate measurement of instability waves in conventional hypersonic facilities can be, in shock tunnels it is appreciably more so. For identical unit Reynolds numbers, the higher stagnation temperature in a shock tunnel means that the dominant second-mode disturbances lie at even higher frequencies (typically hundreds of kHz or higher); moreover, because of the destructive testing environment, hot-wire techniques, a staple for instability measurements in conventional tunnels, cannot be used. Fast-response pressure transducers are an obvious alternative, but recent experiments have highlighted the challenging nature of interpreting data from mechanically sensitive sensors in the high-noise environment of a shock tunnel, especially without accompanying stability computations. Measurements with recently developed atomic-layer thermopile (ALTP) heat-flux sensors show promise, though their use has yet to be demonstrated in shocktunnel facilities.

Item URL in elib:https://elib.dlr.de/71640/
Document Type:Article
Title:Time-Resolved Visualization of Instability Waves in a Hypersonic Boundary Layer
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Laurence, Stuartstuart.laurence (at) dlr.deUNSPECIFIED
Wagner, Alexanderalexander.wagner (at) dlr.deUNSPECIFIED
Hannemann, Klausklaus.hannemann (at) dlr.deUNSPECIFIED
Wartemann, Violaviola.wartemann (at) dlr.deUNSPECIFIED
Lüdeke, Heinrichheinrich.luedeke (at) dlr.deUNSPECIFIED
Journal or Publication Title:AIAA Journal
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.2514/1.J051112
Page Range:pp. 243-246
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:Boundary-layer transition; hypersonic flows
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Raumfahrzeugsysteme - Anlagen u. Messtechnik (old)
Location: Braunschweig , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Laurence, Stuart
Deposited On:28 Nov 2011 11:27
Last Modified:31 Jul 2019 19:33

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