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Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel

Hannemann, Klaus und Martinez Schramm, Jan und Karl, Sebastian und Laurence, Stuart (2015) Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel. 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015-07-06 - 2015-07-09, Glasgow, Scotland, United Kingdom. doi: 10.2514/6.2015-3608.

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Offizielle URL: http://arc.aiaa.org/doi/abs/10.2514/6.2015-3608

Kurzfassung

The free flight force measurement technique is a very attractive tool to determine forces and moments in particular in short duration ground based test facilities. With test times in the order of a few milliseconds, conventional force balances cannot be applied here. The technique has been applied in a number of shock tunnels utilizing models up to approximately 300 mm in length and looking at external aerodynamics. In the present study the technique is applied using a complex 1.5 m long hypersonic integrated supersonic combustion ramjet (scramjet) engine consisting of intake, combustor and thrust nozzle. For scramjet engines the design objective is a combustor with efficient mixing and combustion within the shortest possible length, but still robust enough to operate in various operational conditions. In the framework of the EU co-funded project LAPCAT II, a M=7.4 scramjet powered small scale flight experiment (SSFE) configuration was designed. Since free jet testing of the complete combustion flow path is a mandatory step within the design roadmap of future engines, ground based testing of the SSFE engine was conducted in the High Enthalpy Shock Tunnel Göttingen (HEG) of the German Aerospace Center, DLR. This type of facility allows duplication of flight conditions in excess of M=8. Here tests were performed simulating Mach 7.4 flight conditions in approximately 28 km altitude. The numerically predicted thrust of the engine could be confirmed in HEG utilizing optical tracking of the free flight wind tunnel model. Combining these experimental results with computed aerodynamic data of the complete SSFE showed that for a selected flight condition a positive aero propulsive balance of the complete configuration could be achieved.

elib-URL des Eintrags:https://elib.dlr.de/93538/
Dokumentart:Konferenzbeitrag (Vortrag)
Zusätzliche Informationen:AIAA 2015-3608
Titel:Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Hannemann, Klausklaus.hannemann (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Martinez Schramm, Janjan.martinez (at) dlr.dehttps://orcid.org/0000-0002-8891-6253NICHT SPEZIFIZIERT
Karl, Sebastiansebastian.karl (at) dlr.dehttps://orcid.org/0000-0002-5558-6673NICHT SPEZIFIZIERT
Laurence, Stuartstuart.laurence (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:2015
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
DOI:10.2514/6.2015-3608
Seitenbereich:Seiten 1-15
Name der Reihe:Conference Proceedings online
Status:veröffentlicht
Stichwörter:forces, LAPCAT II, supersonic combustion, high enthalpy
Veranstaltungstitel:20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Veranstaltungsort:Glasgow, Scotland, United Kingdom
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:6 Juli 2015
Veranstaltungsende:9 Juli 2015
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 - Raumfahrzeugsysteme - Anlagen u. Messtechnik (alt)
Standort: Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge
Hinterlegt von: Micknaus, Ilka
Hinterlegt am:28 Aug 2015 12:03
Letzte Änderung:24 Apr 2024 19:59

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