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High Enthalpy Shock Tunnel Testing and Numerical Analysis of Hypersonic Airbreathing Propulsion Configurations

Hannemann, Klaus (2019) High Enthalpy Shock Tunnel Testing and Numerical Analysis of Hypersonic Airbreathing Propulsion Configurations. 1st Brazilian School on Hypersonic Airbreathing Propulsion (scramjet technology), 2019-05-13 - 2019-05-17, Natal, Brasilien.

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Kurzfassung

For future hypersonic transport aircraft or space launch vehicles based on combined cycle engines, the supersonic combustion ramjet (scramjet) is a promising component of the propulsion system. In particular for atmospheric flight Mach numbers in excess of 8, shock tunnel facilities are well suited to duplicate these flight conditions. The focus of the present article is to provide a review of selected important achievements obtained in free piston driven shock tunnel facilities. Research activities conducted in laboratories around the globe will be highlighted followed by a more detailed discussion of the combined experimental and numerical work performed on hydrogen fuelled integrated scramjet configurations at the German Aerospace Center (DLR). The ground based testing was conducted in the High Enthalpy Shock Tunnel Göttingen (HEG) and the computations were performed utilizing the DLR TAU code. Among the considered configurations is the Australian HyShot II flight test vehicle. It is considered to be well suited for fundamental combustor investigations and numerical tool validation purposes. Benchmark data were compiled in HEG related to different combustor modes. These data are related to the nominal operating mode and additionally to the response of the HyShot II combustor to equivalence ratios close to the critical value at which the onset of thermal choking occurs. The detailed analysis of the developing shock train and its unexpected behaviour revealed new insight into the combustor flow generated by localized thermal choking. A small scale flight experiment was designed in the framework of the European Commission co-funded LAPCAT II project. The complete scramjet flow path was subsequently tested in HEG and the numerically predicted positive aero-propulsive balance could be demonstrated by utilizing the free flight force measurement technique based on optical tracking.

elib-URL des Eintrags:https://elib.dlr.de/130015/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:High Enthalpy Shock Tunnel Testing and Numerical Analysis of Hypersonic Airbreathing Propulsion Configurations
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Hannemann, KlausKlaus.Hannemann (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:13 Mai 2019
Referierte Publikation:Nein
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Status:veröffentlicht
Stichwörter:supersonic combustion ramjet, free piston driven shock tunnel, hydrogen combustion, ground based testing, numerical modelling
Veranstaltungstitel:1st Brazilian School on Hypersonic Airbreathing Propulsion (scramjet technology)
Veranstaltungsort:Natal, Brasilien
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:13 Mai 2019
Veranstaltungsende:17 Mai 2019
Veranstalter :Universidade Federal do Rio Grande do Norte (UFRN) School of Sciences and Technology
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:08 Nov 2019 16:57
Letzte Änderung:24 Apr 2024 20:33

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