Shock effects on delta wing vortex breakdown
2009 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 46, no 3, 903-914 p.Article in journal (Refereed) Published
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 to examine this behavior 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 are examined to provide an explanation of the sensitivity of the breakdown location. Limited experimental data are available to supplement the computational fluid dynamics results in certain key respects, and the ideal synergy between computational fluid dynamics and experiments for this problem is considered.
Place, publisher, year, edition, pages
2009. Vol. 46, no 3, 903-914 p.
Angle of Incidence, Delta wing vortices, Delta wings, Experimental data, Free-stream, Shock strength, Vortex breakdown location, Vortex strength, Delta wing aircraft, Fluid dynamics
IdentifiersURN: urn:nbn:se:kth:diva-8479DOI: 10.2514/1.38792ISI: 000266894200017ScopusID: 2-s2.0-67651065245OAI: oai:DiVA.org:kth-8479DiVA: diva2:13814
QC 20100713. Uppdaterad från konferensbidrag till artikel (20100713).2008-05-162008-05-162014-10-13Bibliographically approved