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Accurate physical and numerical modeling of complex vortex phenomena over delta wings
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
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 [en]
computational fluid dynamics, CFD, vortical flow, delta wing, aerodynamics, flow physics, steady, unsteady
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-4164OAI: oai:DiVA.org:kth-4164DiVA: diva2:11006
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
List of papers
1. Numerical investigation of Reynolds number effects on a blunt leading-edge delta wing
Open this publication in new window or tab >>Numerical investigation of Reynolds number effects on a blunt leading-edge delta wing
2006 (English)In: 24th AIAA Applied Aerodynamics Conference: San Francisco, CA : 5 June 2006 through 8 June 2006, 2006, 708-726 p.Conference paper, Published paper (Refereed)
Abstract [en]

Numerical results are presented and discussed in this paper allowing a deeper and more precise characterization of the unique double vortex system, which develops on the second International Vortex Flow Experiment (VFE-2) blunt leading edge delta wing of 65° sweep. Computational fluid dynamic (CFD) computations have been performed for three Reynolds numbers (2, 6 and 60 million) at three angles of attack (13.3°, 18.5° and 23.0°) for a fixed Mach number of 0.4. Leading edge primary separation onset is shown to match best the available wind tunnel data at the highest investigated Reynolds number of 60 million and at an angle of attack of 23.0°. At this condition, the coupling between outer primary vortex attachment line with the inner primary vortex separation line is clearly recognizable. Only if the inner primary vortex strength is predicted well, the attached flow passing under the inner primary vortex core is accelerated sufficiently to trigger (inner) secondary separation.

Series
Collection of Technical Papers : AIAA Applied Aerodynamics Conference, ISSN 1048-5953
Keyword
Angle measurement; Computational fluid dynamics; Delta wing aircraft; Numerical methods; Vortex flow; Wind tunnels; Mach numbers; Secondary separation; Vortex strength
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-8476 (URN)2-s2.0-33845409766 (Scopus ID)978-156347812-3 (ISBN)
Note
QC 20100713Available from: 2008-05-16 Created: 2008-05-16 Last updated: 2010-07-13Bibliographically approved
2. Initial Steady and Unsteady CFD Analysis of a Half-span Delta Wing
Open this publication in new window or tab >>Initial Steady and Unsteady CFD Analysis of a Half-span Delta Wing
2006 (English)In: Proceedings of the 25th Congress of the International Council of the Aeronautical Sciences 2006, 2006Conference paper, Published paper (Refereed)
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6323 (URN)9781604232271 (ISBN)
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

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Citation style
  • apa
  • harvard1
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  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
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  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
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  • text
  • asciidoc
  • rtf