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Initial Steady and Unsteady CFD Analysis of a Half-span Delta Wing
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2006 (English)In: Proceedings of the 25th Congress of the International Council of the Aeronautical Sciences 2006, 2006Conference paper, Published paper (Refereed)
Place, publisher, year, edition, pages
2006.
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-6323ISBN: 9781604232271 (print)OAI: oai:DiVA.org:kth-6323DiVA: diva2:11005
Conference
25th Congress of the International Council of the Aeronautical Sciences, 3-8 September 2006, Hamburg, Germany
Note
QC 20101111Available from: 2006-11-07 Created: 2006-11-07 Last updated: 2010-11-11Bibliographically approved
In thesis
1. Accurate physical and numerical modeling of complex vortex phenomena over delta wings
Open this publication in new window or tab >>Accurate physical and numerical modeling of complex vortex phenomena over delta wings
2006 (English)Licentiate thesis, comprehensive summary (Other scientific)
Abstract [en]

With this contribution to the AVT-113/VFE-2 task group it was possible to prove the feasibility of high Reynolds number CFD computations to resolve and thus better understand the peculiar dual vortex system encountered on the VFE-2 blunt leading edge delta wing. Initial investigations into this phenomenon seemed to undermine the hypothesis, that the formation of the inner vortex system relies on the laminar state of the boundary layer at separation onset. As a result of this research, this initial hypothesis had to be expanded to account also for high Reynolds number cases, where a laminar boundary layer status at separation onset could be excluded. Furthermore, the data published in the same context shows evidence of secondary separation under the inner primary vortex. This further supports the supposition of a different generation mechanism of the inner vortical system other than a pure development out of a possibly laminar separation bubble. The unsteady computations performed on numerical grids with different levels of refinement led furthermore to the establishment of internal guidelines specific to the DES approach.

Place, publisher, year, edition, pages
Stockholm: KTH, 2006. v, 19 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2006:82
Keyword
computational fluid dynamics, CFD, vortical flow, delta wing, aerodynamics, flow physics, steady, unsteady
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-4164 (URN)
Presentation
2006-11-27, Seminarierum S40, AVE, Teknikringen 8, Stockholm, 13:00
Opponent
Supervisors
Note
QC 20101111Available from: 2006-11-07 Created: 2006-11-07 Last updated: 2010-11-11Bibliographically approved

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Citation style
  • apa
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More styles
Language
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  • Other locale
More languages
Output format
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