Supersonic fin-body interactions in an internal scramjet flow

Lorrain, Philippe and Boyce, Russell (2011) Supersonic fin-body interactions in an internal scramjet flow. Journal of Propulsion and Power, 27 2: 319-329. doi:10.2514/1.49226


Author Lorrain, Philippe
Boyce, Russell
Title Supersonic fin-body interactions in an internal scramjet flow
Journal name Journal of Propulsion and Power   Check publisher's open access policy
ISSN 0748-4658
1533-3876
Publication date 2011-01-01
Year available 2011
Sub-type Article (original research)
DOI 10.2514/1.49226
Open Access Status Not yet assessed
Volume 27
Issue 2
Start page 319
End page 329
Total pages 11
Place of publication Reston, VA United States
Publisher American Institute of Aeronautics and Astronautics, Inc.
Language eng
Subject 2202 History and Philosophy of Specific Fields
1912 Space and Planetary Science
2103 Historical Studies
2210 Mechanical Engineering
Abstract This paper reports on the study of a fin-body junction flow in the context of an internal scramjet flowpath. Threedimensional Reynolds-averaged Navier-Stokes numerical simulations of the flowfield inside a particular scramjet configuration have been performed using the commercial computational fluid dynamics code CFD++. The junction is formed by a central strut fuel injector spanning the entrance to a direct-connect combustor. The local flow Mach number is 2.5. The bow shock generated by the blunt strut injector causes flow separation on the side wall, which leads to the formation of horseshoe vortices. The computed results in the symmetry plane and on the injector surface near the leading edge of the strut are in good agreement with the solutions obtained by other investigators for isolated fin-body junctions. Further downstream, reflections of the strut bow shock at the internal flow top wall and then the strut surface have significant effect on the propagation of the fin-body interaction. The shock-vortex interaction was found to despin the primary horseshoe vortex; i.e., oppositely orientated vorticity is induced, and hence dissipate vorticity. Further reduction of the vorticity, associated with the observed vortices, occurs due to viscous dissipation of the horseshoe vortices in the internal flow side wall boundary layer.
Q-Index Code C1
Q-Index Status Provisional Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collection: School of Mechanical & Mining Engineering Publications
 
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