Performance Assessment of Transition Models for Three-Dimensional Flow Over NACA4412 Wings at Low Reynolds Numbers

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dc.authoridKarasu, Ilyas/0000-0003-3138-6236
dc.authoridGENC, Mustafa Serdar/0000-0002-6540-620X
dc.authoridOzden, Mustafa/0000-0002-7650-1632
dc.contributor.authorKarasu, Ilyas
dc.contributor.authorOzden, Mustafa
dc.contributor.authorGenc, Mustafa Serdar
dc.date.accessioned2025-01-06T17:44:39Z
dc.date.available2025-01-06T17:44:39Z
dc.date.issued2018
dc.description.abstractThe performance of the transition models on three-dimensional (3D) flow of wings with aspect ratios (AR) of 1 and 3 at low Reynolds number was assessed in this study. For experimental work; force measurements, surface oil and smoke-wire flow visualizations were performed over the wings with NACA4412 section at Reynolds numbers of 2.5 x 10(4), 5 x 10(4), and 7.5 x 10(4) and the angles of attack of 8 deg, 12 deg, and 20 deg. Results showed that the AR had significant effects on the 3D flow structure over the wing. According to the experimental and numerical results, the flow over the wing having lower ARs can be defined with wingtip vortices, axial flow, and secondary flow including spiral vortex inside the separated flow. When the angle of attack and Reynolds number was increased, wing-tip vortices were enlarged and interacted with the axial flow. At higher AR, flow separation was dominant, whereas wing-tip vortices suppressed the flow separation over the wing with lower AR. In the numerical results, while there were some inconsistencies in the prediction of lift coefficients, the predictions of drag coefficients for two transition models were noticeably better. The performance of the transition models judged from surface patterns was good, but the k-k(L)-omega was preferable. Secondary flow including spiral vortices near the surface was predicted accurately by the k-k(L)-omega. Consequently, in comparison with experiments, the predictions of the k-k(L)-omega were better than those of the shear stress transport (SST) transition.
dc.description.sponsorshipScientific and Technological Research Council of Turkey (TUBITAK) [213M329]
dc.description.sponsorshipScientific and Technological Research Council of Turkey (TUBITAK) under the Project No. 213M329.
dc.identifier.doi10.1115/1.4040228
dc.identifier.issn0098-2202
dc.identifier.issn1528-901X
dc.identifier.issue12
dc.identifier.scopus2-s2.0-85051087101
dc.identifier.scopusqualityQ2
dc.identifier.urihttps://doi.org/10.1115/1.4040228
dc.identifier.urihttps://hdl.handle.net/20.500.14669/3137
dc.identifier.volume140
dc.identifier.wosWOS:000448235800002
dc.identifier.wosqualityQ3
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherAsme
dc.relation.ispartofJournal of Fluids Engineering-Transactions of The Asme
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_20241211
dc.subjecttransition models
dc.subjectcomputational fluid dynamics
dc.subjectlaminar separation bubble
dc.subjecttip vortex
dc.titlePerformance Assessment of Transition Models for Three-Dimensional Flow Over NACA4412 Wings at Low Reynolds Numbers
dc.typeArticle

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