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Shock effects on delta wing vortex breakdown
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
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2008 (English)In: 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008Conference paper, Published paper (Refereed)
Abstract [en]

It has been observed that delta wings placed in a transonic freestream can experience a sudden movement of the vortex breakdown location as the angle of incidence is increased. The current paper uses Computational Fluid Dynamics (CFD) to examine this behaviour in detail. The study shows that a shock-vortex interaction is responsible. The balance of the vortex strength and axial flow, and the shock strength, is examined to provide an explanation of the sensitivity of the breakdown location. Limited experimental data is available to supplement the CFD results in certain key respects, and the ideal synergy between CFD and experiments for this problem is considered.

Place, publisher, year, edition, pages
2008.
Keyword [en]
Angle of Incidence, Delta wing vortices, Delta wings, Experimental data, Free-stream, Shock strength, Vortex breakdown location, Vortex strength
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-154049DOI: 10.2514/6.2008-395Scopus ID: 2-s2.0-78149434306ISBN: 9781563479373 (print)OAI: oai:DiVA.org:kth-154049DiVA: diva2:754889
Conference
46th AIAA Aerospace Sciences Meeting and Exhibit; Reno, NV; United States; 7 January 2008 through 10 January 2008
Note

QC 20141013

Available from: 2014-10-13 Created: 2014-10-13 Last updated: 2014-10-13Bibliographically approved

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Citation style
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  • nn-NB
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  • Other locale
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Output format
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  • asciidoc
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