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

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

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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.

Titel:Time-Resolved Visualization of Instability Waves in a Hypersonic Boundary Layer
AutorenInstitution oder E-Mail-Adresse der Autoren
Laurence, Stuartstuart.laurence@dlr.de
Wagner, Alexanderalexander.wagner@dlr.de
Hannemann, Klausklaus.hannemann@dlr.de
Wartemann, Violaviola.wartemann@dlr.de
Lüdeke, Heinrichheinrich.luedeke@dlr.de
Tanno, HideyukiJAXA
Itoh, KatsuhiroJAXA
Erschienen in:AIAA Journal
Referierte Publikation:Ja
In Open Access:Nein
In ISI Web of Science:Ja
DOI :10.2514/1.J051112
Seitenbereich:Seiten 243-246
Verlag:The American Institute of Aeronautics and Astronautics (AIAA)
Stichwörter:Boundary-layer transition; hypersonic flows
HGF - Forschungsbereich:Verkehr und Weltraum (alt)
HGF - Programm:Weltraum (alt)
HGF - Programmthema:W RP - Raumtransport
DLR - Schwerpunkt:Weltraum
DLR - Forschungsgebiet:W RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):W - Raumfahrzeugsysteme - Anlagen u. Messtechnik (alt)
Standort: Braunschweig , Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge
Hinterlegt von: Stuart Laurence
Hinterlegt am:28 Nov 2011 11:27
Letzte Änderung:20 Apr 2015 08:39

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