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Free Piston Shock Tunnels HEG, HIEST, T4 and T5

Hannemann, Klaus and Itoh, Katsuhiro and Mee, D. J. and Hornung, Hans G. (2016) Free Piston Shock Tunnels HEG, HIEST, T4 and T5. In: Experimental Methods of Shock Wave Research Shock Wave Science and Technology Reference Library, 9. Springer Verlag, Cham. pp. 181-264. ISBN 978-3-319-23744-2.

Full text not available from this repository.

Official URL: https://doi.org/10.1007/978-3-319-23745-9_7

Abstract

In hypervelocity flows the speed of the considered fluid is much larger than the speed of sound. Commonly the hypersonic flow regime is considered to start above a Mach number, M, of 5. Ground based testing of such flows is performed in many different types of facilities. The reason for this is the large range of flow conditions and phenomena encountered in hypersonic flight and the fact that no single facility can simulate all relevant flow parameters simultaneously. Therefore, in hypersonic testing, partial simulation of different flow phenomena is performed in different types of facilities. Examples are Mach-Reynolds number simulation in cold hypersonic ground based test facilities, verification and qualification of hot structures of space vehicles in arc–heated test facilities or the investigation of the influence of the chemically reacting flow past an entry or re-entry vehicle on its aerodynamic behaviour in shock tunnels or shock expansion tunnels. In the present article, the operating principle of free piston driven shock tunnels is presented and examples of research in the worldwide largest facilities is discussed.

Item URL in elib:https://elib.dlr.de/92824/
Document Type:Contribution to a Collection
Additional Information:Print ISBN 978-3-319-23744-2 Online ISBN 978-3-319-23745-9
Title:Free Piston Shock Tunnels HEG, HIEST, T4 and T5
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Hannemann, Klausklaus.hannemann (at) dlr.deUNSPECIFIED
Itoh, KatsuhiroJapan Aerospace Exploration Agency, JAXA, Kakuda Space Center, Kakuda Miyagi 981-1525 JapanUNSPECIFIED
Mee, D. J.The University of Queensland, Centre for Hypersonics, School of Mechanical and MiningUNSPECIFIED
Hornung, Hans G.California Institute of Technology, Pasadena, CAUNSPECIFIED
Date:2016
Journal or Publication Title:Experimental Methods of Shock Wave Research
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
Volume:9
DOI :10.1007/978-3-319-23745-9_7
Page Range:pp. 181-264
Editors:
EditorsEmail
Igra, OzerUNSPECIFIED
Seiler, FriedrichUNSPECIFIED
Publisher:Springer Verlag, Cham
Series Name:Shock Wave Science and Technology Reference Library
ISBN:978-3-319-23744-2
Status:Published
Keywords:Free Piston Shock Tunnels; RE-ENTRY, hypersonic boundary layer transition, supersonic combustion ramjet, Mach number, Shock tube, Incident shock wave, Shock tunnel, Shock train
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Wiederverwendbare Raumfahrtsysteme und Antriebstechnologie
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Deposited By: Hannemann, Prof. Dr. Klaus
Deposited On:15 Nov 2018 10:19
Last Modified:27 Sep 2019 09:36

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