Near-surface particle image velocimetry measurements over a yawed slender delta wing

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dc.authoridKarasu, Ilyas/0000-0003-3138-6236
dc.authoridSahin, Besir/0000-0003-0671-0890
dc.contributor.authorKarasu, Ilyas
dc.contributor.authorTumse, Sergen
dc.contributor.authorTasci, Mehmat O.
dc.contributor.authorSahin, Besir
dc.contributor.authorAkilli, Huseyin
dc.date.accessioned2025-01-06T17:36:21Z
dc.date.available2025-01-06T17:36:21Z
dc.date.issued2021
dc.description.abstractIn this study, extensive instantaneous velocity measurements were conducted within a flow area by stereo particle image velocimetry (SPIV) to investigate the influence of the yaw angle, beta, on the vortical flow structure formed on a slender delta wing. This sideslip angle, beta, in the yaw plane was varied from 4 degrees up to 20 degrees with an interval of 4 degrees at two critical angles of attack, alpha = 25 degrees and 35 degrees, respectively. In order to reveal the influence of the yaw angle, beta over the flow structure of the delta wing, time-averaged flow statistics, and instantaneous flow data obtained by the SPIV technique in the plan-view plane close to the suction surface of the delta wing were presented. It was observed that even a low yaw angle, for instance beta = 8 degrees, becomes to be effective on the flow characteristics of the delta wing, and this effect was augmented with increasing beta. The influence of beta is quite high on the vortical flow structure at alpha= 35 degrees compared to the angle of attack of alpha = 25 degrees. The flow structure that is symmetrical with respect to the centerline of the wing in the case of no yaw has disrupted with the existence beta. Furthermore, the extent of the asymmetry enlarges with increasing beta. The leading-edge vortex (LEV) on the windward side broken earlier and dominated the flow on the wing surface. It is concluded that this asymmetric flow structure can deteriorate the aerodynamic performance and cause other adverse effects such as unsteady loading.
dc.description.sponsorshipScientific and Technological Research Council of Turkey (TUBITAK) [114M497]; Cukurova University Scientific Research Unit [MMF2013D9]
dc.description.sponsorshipThe author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: The authors are grateful to the Scientific and Technological Research Council of Turkey (TUBITAK) under contract number of 114M497 and Cukurova University Scientific Research Unit under contract number of MMF2013D9 for the support for this investigation.
dc.identifier.doi10.1177/0954410021999556
dc.identifier.endpage2478
dc.identifier.issn0954-4100
dc.identifier.issn2041-3025
dc.identifier.issue16
dc.identifier.scopus2-s2.0-85102467670
dc.identifier.scopusqualityQ3
dc.identifier.startpage2466
dc.identifier.urihttps://doi.org/10.1177/0954410021999556
dc.identifier.urihttps://hdl.handle.net/20.500.14669/1835
dc.identifier.volume235
dc.identifier.wosWOS:000682553300001
dc.identifier.wosqualityQ4
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherSage Publications Ltd
dc.relation.ispartofProceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_20241211
dc.subjectAngle of attack
dc.subjectDelta wing
dc.subjectStereo particle image velocimetry
dc.subjectVortical flow
dc.subjectYaw angle
dc.titleNear-surface particle image velocimetry measurements over a yawed slender delta wing
dc.typeArticle

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