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Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes

Flock, Andreas K. und Gülhan, Ali (2016) Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes. AIAA Journal, 54 (6), Seiten 1881-1891. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.J054287. ISSN 0001-1452.

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Kurzfassung

During Busemann intake design, two constraints have to be considered. First, caused by the displacement of the boundary layer, the pressure levels in a Busemann intake were higher (≈40%) than the values predicted analytically; these effects were labeled viscous effects. Second, truncating the flowfield also changed the properties of the classical Busemann flow; these effects were labeled truncation effects, and it can be distinguished between truncating the intake at the leading edge and at the rear side. To take into account viscous effects, the boundary-layer displacement thickness was calculated with an integral method and added to the inviscid Busemann contour. To quantify leadingedge truncation effects, an oblique shock at the leading edge was assumed, and the pressure at the intake exit was corrected with the continuity equation. The change in flow properties during the rear-side truncation was calculated with a stream-thrust analysis. The effects were separately investigated with Reynolds-averaged Navier–Stokes and Euler simulations, respectively. After the viscous correction, the deviation between numerically and analytically calculated pressure level was below 10%.When truncating the intake, the numerically calculated average pressure and temperature levels were within 1% of the analytical values.

elib-URL des Eintrags:https://elib.dlr.de/106371/
Dokumentart:Zeitschriftenbeitrag
Titel:Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Flock, Andreas K.andreas.flock (at) dlr.dehttps://orcid.org/0000-0002-0507-2420NICHT SPEZIFIZIERT
Gülhan, AliAli.Guelhan (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:18 April 2016
Erschienen in:AIAA Journal
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Ja
Band:54
DOI:10.2514/1.J054287
Seitenbereich:Seiten 1881-1891
Verlag:American Institute of Aeronautics and Astronautics (AIAA)
ISSN:0001-1452
Status:veröffentlicht
Stichwörter:Scramjet, Hypersonic Propulsion, Intake Design
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:24 Okt 2016 12:25
Letzte Änderung:27 Nov 2023 12:54

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