Versenden
Drucken
Hannemann, Klaus und Itoh, Katsuhiro und Mee, D. J. und 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. Seiten 181-264. doi: 10.1007/978-3-319-23745-9_7. ISBN 978-3-319-23744-2.
Dieses Archiv kann nicht den Volltext zur Verfügung stellen.
Offizielle URL: https://doi.org/10.1007/978-3-319-23745-9_7
Kurzfassung
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.
| elib-URL des Eintrags: | https://elib.dlr.de/92824/ | ||||||||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Dokumentart: | Beitrag im Sammelband | ||||||||||||||||||||
| Zusätzliche Informationen: | Print ISBN 978-3-319-23744-2 Online ISBN 978-3-319-23745-9 | ||||||||||||||||||||
| Titel: | Free Piston Shock Tunnels HEG, HIEST, T4 and T5 | ||||||||||||||||||||
| Autoren: |
| ||||||||||||||||||||
| Datum: | 2016 | ||||||||||||||||||||
| Erschienen in: | Experimental Methods of Shock Wave Research | ||||||||||||||||||||
| Referierte Publikation: | Ja | ||||||||||||||||||||
| Open Access: | Nein | ||||||||||||||||||||
| Gold Open Access: | Nein | ||||||||||||||||||||
| In SCOPUS: | Ja | ||||||||||||||||||||
| In ISI Web of Science: | Nein | ||||||||||||||||||||
| Band: | 9 | ||||||||||||||||||||
| DOI: | 10.1007/978-3-319-23745-9_7 | ||||||||||||||||||||
| Seitenbereich: | Seiten 181-264 | ||||||||||||||||||||
| Herausgeber: |
| ||||||||||||||||||||
| Verlag: | Springer Verlag, Cham | ||||||||||||||||||||
| Name der Reihe: | Shock Wave Science and Technology Reference Library | ||||||||||||||||||||
| ISBN: | 978-3-319-23744-2 | ||||||||||||||||||||
| Status: | veröffentlicht | ||||||||||||||||||||
| Stichwörter: | 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 - Forschungsbereich: | Luftfahrt, Raumfahrt und Verkehr | ||||||||||||||||||||
| HGF - Programm: | Raumfahrt | ||||||||||||||||||||
| HGF - Programmthema: | Raumtransport | ||||||||||||||||||||
| DLR - Schwerpunkt: | Raumfahrt | ||||||||||||||||||||
| DLR - Forschungsgebiet: | R RP - Raumtransport | ||||||||||||||||||||
| DLR - Teilgebiet (Projekt, Vorhaben): | R - Wiederverwendbare Raumfahrtsysteme und Antriebstechnologie | ||||||||||||||||||||
| Standort: | Göttingen | ||||||||||||||||||||
| Institute & Einrichtungen: | Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge, GO | ||||||||||||||||||||
| Hinterlegt von: | Hannemann, Prof. Dr. Klaus | ||||||||||||||||||||
| Hinterlegt am: | 15 Nov 2018 10:19 | ||||||||||||||||||||
| Letzte Änderung: | 27 Sep 2019 09:36 |
Nur für Mitarbeiter des Archivs: Kontrollseite des Eintrags
