elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Contact | Deutsch
Fontsize: [-] Text [+]

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, Vol. 5 (1), pp. 243-246. The American Institute of Aeronautics and Astronautics (AIAA). DOI: 10.2514/1.J051112.

[img]
Preview
PDF - Requires a PDF viewer such as GSview, Xpdf or Adobe Acrobat Reader
351kB
[img]
Preview
HTML
351kB

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

Abstract

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.

Document Type:Article
Title:Time-Resolved Visualization of Instability Waves in a Hypersonic Boundary Layer
Authors:
AuthorsInstitution or Email of Authors
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
Date:2012
Journal or Publication Title:AIAA Journal
Refereed publication:Yes
In Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:Vol. 5
DOI:10.2514/1.J051112
Page Range:pp. 243-246
Publisher:The American Institute of Aeronautics and Astronautics (AIAA)
Status:Published
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: Stuart Laurence
Deposited On:28 Nov 2011 11:27
Last Modified:12 Dec 2013 21:24

Repository Staff Only: item control page

Browse
Search
Help & Contact
Informationen
electronic library is running on EPrints 3.3.12
Copyright © 2008-2012 German Aerospace Center (DLR). All rights reserved.