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Experimental and Numerical Performance Analysis of a Self Starting, Three-Dimensional SCRamjet Intake

Flock, Andreas K und Gülhan, Ali (2015) Experimental and Numerical Performance Analysis of a Self Starting, Three-Dimensional SCRamjet Intake. In: 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015. 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 06.-09. Jul. 2015, Glasgow, Schottland. doi: 10.2514/6.2015-3680.

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Kurzfassung

In the present paper, a three-dimensional intake model is investigated in a blow-down wind tunnel and results are compared and complemented with numerical simulations (Reynolds-averaged Navier-Stokes simulations). The intake model was equipped with a movable cowl and therefore the internal contraction ratio was variable and was adjusted to the self starting condition. Three different conditions were investigated: i) at a free stream Mach number of 7, a v-shaped cowl geometry was investigated, ii) at a free stream Mach number of 7 a straight cowl geometry was investigated, and iii) the v-shaped cowl geometry was investigated at a free stream Mach number of 6. Furthermore a one-dimensional post analysis was performed, to calculate overall engine parameter from stream thrust averaged intake performance parameter. The numerical simulations were validated on the basis of wall pressure and rake pressure measurements and the match was generally well. Performance wise, the v-shaped cowl was slightly superior compared to the straight cowl. For the Mach 7 configurations maximum back pressure ratios of approximately 120 were measured, which is about 4 times the nominal operating pressure ratio. For the Mach 6 case, the maximum static back pressure ratio dropped to about 80, which again is approximately 4 times the nominal operating pressure ratio.

elib-URL des Eintrags:https://elib.dlr.de/97944/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Experimental and Numerical Performance Analysis of a Self Starting, Three-Dimensional SCRamjet Intake
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Flock, Andreas Kandreas.flock (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Gülhan, AliAli.Guelhan (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:Juli 2015
Erschienen in:20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Referierte Publikation:Nein
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Nein
DOI:10.2514/6.2015-3680
Status:veröffentlicht
Stichwörter:scramjet, hypersonics, intake, wind tunnel testing
Veranstaltungstitel:20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Veranstaltungsort:Glasgow, Schottland
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:06.-09. Jul. 2015
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:keine Zuordnung
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R - keine Zuordnung
DLR - Teilgebiet (Projekt, Vorhaben):R - keine Zuordnung
Standort: Köln-Porz
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Über- und Hyperschalltechnologien
Hinterlegt von: Flock, Andreas
Hinterlegt am:31 Aug 2015 10:29
Letzte Änderung:19 Jul 2023 14:00

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