Experimental Investigation of Ground Effect on the Vortical Flow Structure of a 40° Swept Delta Wing

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dc.authoridKarasu, Ilyas/0000-0003-3138-6236
dc.authoridSahin, Besir/0000-0003-0671-0890
dc.contributor.authorTumse, Sergen
dc.contributor.authorKarasu, Ilyas
dc.contributor.authorSahin, Besir
dc.date.accessioned2025-01-06T17:38:18Z
dc.date.available2025-01-06T17:38:18Z
dc.date.issued2022
dc.description.abstractThe ground effect influences the flow structure on a delta wing during landing and take-off processes. In this regard, comprehensive instantaneous velocity measurements and flow visualizations were carried out by particle image velocimetry and dye flow visualization techniques to reveal the ground effect on leading-edge vortex characteristics of a 40 degrees swept delta wing. The flow behaviors on the delta wing under the impact of the ground were analyzed at two angles of attack, 8 degrees and 11 degrees, and the space between the ground and lower surface of the wing was nondimensionalized with the wing's chord length. It was found that the presence of the ground caused premature leading-edge vortex breakdown due to the increasing adverse pressure gradient on the wing's suction side along the chord direction. The ground effect caused an increase in peak value and distributions of turbulent kinetic energy on the wing surface that depended on the earlier leading-edge vortex bursting and complex and disorganized flow structures. The value of time-averaged vertical velocity was lower when the delta wing descended from the free-stream flow zone into the ground effect zone because of the blocking of fluid flow in the gap between the ground and pressure surface of the wing. Thus, it can be concluded that the ground effect is very influential on the change of vortical flow characteristics of nonslender delta wings.
dc.description.sponsorshipScientific Researched Project Office of Cukurova University [FYL-2019-11369]
dc.description.sponsorshipThe authors would like to acknowledge the Scientific Researched Project Office of Cukurova University for their support under Contract No. FYL-2019-11369.
dc.identifier.doi10.1061/(ASCE)AS.1943-5525.0001441
dc.identifier.issn0893-1321
dc.identifier.issn1943-5525
dc.identifier.issue4
dc.identifier.scopus2-s2.0-85130217701
dc.identifier.scopusqualityQ2
dc.identifier.urihttps://doi.org/10.1061/(ASCE)AS.1943-5525.0001441
dc.identifier.urihttps://hdl.handle.net/20.500.14669/2527
dc.identifier.volume35
dc.identifier.wosWOS:000796078600017
dc.identifier.wosqualityQ2
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherAsce-Amer Soc Civil Engineers
dc.relation.ispartofJournal of Aerospace Engineering
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_20241211
dc.subjectGround effect
dc.subjectLeading-edge vortex
dc.subjectNonslender delta wing
dc.subjectParticle image velocimetry (PIV)
dc.subjectVortical flow
dc.titleExperimental Investigation of Ground Effect on the Vortical Flow Structure of a 40° Swept Delta Wing
dc.typeArticle

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