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Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes

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

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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.

Item URL in elib:https://elib.dlr.de/106371/
Document Type:Article
Title:Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Flock, Andreas Kandreas.flock (at) dlr.deUNSPECIFIED
Gülhan, AliAli.Guelhan (at) dlr.deUNSPECIFIED
Date:18 April 2016
Journal or Publication Title:AIAA Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.2514/1.J054287
Page Range:pp. 1881-1891
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:Scramjet, Hypersonic Propulsion, Intake Design
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:other
DLR - Research area:Raumfahrt
DLR - Program:R - no assignment
DLR - Research theme (Project):R - no assignment
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Über- und Hyperschalltechnologien
Deposited By: Flock, Andreas
Deposited On:24 Oct 2016 12:25
Last Modified:08 Mar 2018 18:42

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