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High Enthalpy, High Pressure Short Duration Testing of Hypersonic Flows

Hannemann, Klaus and Martinez Schramm, Jan (2007) High Enthalpy, High Pressure Short Duration Testing of Hypersonic Flows. In: Springer Handbook of Experimental Fluid Mechanics Springer-Verlag Berlin Heidelberg. pp. 1081-1125. ISBN 978-3-540-25141-5.

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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 of M=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. In the present chapter, the basic working principle of different types of shock tunnels and shock expansion tunnels, the special aspects of measurement techniques in such short duration facilities with test times of approximately 5 milliseconds and less and some selected typical applications in existing facilities will be discussed.

Document Type:Book Section
Title:High Enthalpy, High Pressure Short Duration Testing of Hypersonic Flows
AuthorsInstitution or Email of Authors
Hannemann, KlausUNSPECIFIED
Martinez Schramm, JanUNSPECIFIED
Journal or Publication Title: Springer Handbook of Experimental Fluid Mechanics
Refereed publication:No
In ISI Web of Science:No
Page Range:pp. 1081-1125
Tropea, CameronUNSPECIFIED
Yarin, AlexanderUNSPECIFIED
Publisher:Springer-Verlag Berlin Heidelberg
Keywords:short duration testing, hypersonic, high enthalpy, measurement techniques, shock tunnels, shock expansion tunnels,
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 - Grundlagen Raumtransport - Anlagen und Messtechnik (old)
Location: Braunschweig , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Dagmar Brennecke-Hosseinzadeh
Deposited On:27 Nov 2007
Last Modified:15 Jan 2010 00:25

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