Please use this identifier to cite or link to this item: https://hdl.handle.net/20.500.11851/6730
Full metadata record
DC FieldValueLanguage
dc.contributor.authorGenç, M. Serdar-
dc.contributor.authorKaynak, Ünver-
dc.contributor.authorLock, G. D.-
dc.date.accessioned2021-09-11T15:43:20Z-
dc.date.available2021-09-11T15:43:20Z-
dc.date.issued2009en_US
dc.identifier.issn0954-4100-
dc.identifier.issn2041-3025-
dc.identifier.urihttps://doi.org/10.1243/09544100JAERO434-
dc.identifier.urihttps://hdl.handle.net/20.500.11851/6730-
dc.description.abstractIn this study, a multi-element aerofoil including NACA2415 aerofoil with NACA22 leading-edge slat is experimentally and computationally investigated at a transitional Reynolds number of 2 x 10(5). In the experiment, the single-element aerofoil experiences a laminar separation bubble, and a maximum lift coefficient of 1.3 at a stall angle of attack of 12 degrees is obtained. This flow has been numerically simulated by FLUENT, employing the recently developed, k-k(L)-omega and k-omega shear-stress transport (SST) transition models. Both transition models are shown to accurately predict the location of the experimentally determined separation bubble. Experimental measurements also illustrate that the leading-edge slat significantly delays the stall up to an angle of attack of 20 degrees, with a maximum lift coefficient of 1.9. The fluid dynamics governing this improvement is the elimination of the separation bubble by the injection of high momentum fluid through the slat over the main aerofoil - an efficient means of flow control. Numerical simulations using k-k(L)-omega are shown to accurately predict the lift curve, including stall, but not the complete elimination of the separation bubble. Conversely, the lift curve prediction using the k-omega SST transition model is less successful, but the separation bubble is shown to fully vanish in agreement with the experiment.en_US
dc.description.sponsorshipFoundation of Erciyes UniversityErciyes Universityen_US
dc.description.sponsorshipM. S. Genc thanks the Foundation of Erciyes University for funding of visiting to the Bath University as academic visitor.en_US
dc.language.isoenen_US
dc.publisherSage Publications Ltden_US
dc.relation.ispartofProceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineeringen_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.subjectleading-edge slaten_US
dc.subjectseparation bubbleen_US
dc.subjectflow separation controlen_US
dc.subjecttransition modelsen_US
dc.subjectwind tunnelen_US
dc.titleFlow Over an Aerofoil Without and With a Leading-Edge Slat at a Transitional Reynolds Numberen_US
dc.typeArticleen_US
dc.departmentFaculties, Faculty of Engineering, Department of Mechanical Engineeringen_US
dc.departmentFakülteler, Mühendislik Fakültesi, Makine Mühendisliği Bölümütr_TR
dc.identifier.volume223en_US
dc.identifier.issueG3en_US
dc.identifier.startpage217en_US
dc.identifier.endpage231en_US
dc.authorid0000-0002-6540-620X-
dc.identifier.wosWOS:000266307700003en_US
dc.identifier.scopus2-s2.0-69249134645en_US
dc.institutionauthorKaynak, Ünver-
dc.identifier.doi10.1243/09544100JAERO434-
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.identifier.scopusqualityQ2-
item.openairetypeArticle-
item.languageiso639-1en-
item.grantfulltextnone-
item.fulltextNo Fulltext-
item.openairecristypehttp://purl.org/coar/resource_type/c_18cf-
item.cerifentitytypePublications-
crisitem.author.dept02.7. Department of Mechanical Engineering-
Appears in Collections:Makine Mühendisliği Bölümü / Department of Mechanical Engineering
Scopus İndeksli Yayınlar Koleksiyonu / Scopus Indexed Publications Collection
WoS İndeksli Yayınlar Koleksiyonu / WoS Indexed Publications Collection
Show simple item record



CORE Recommender

SCOPUSTM   
Citations

54
checked on Dec 21, 2024

WEB OF SCIENCETM
Citations

69
checked on Oct 5, 2024

Page view(s)

84
checked on Dec 23, 2024

Google ScholarTM

Check




Altmetric


Items in GCRIS Repository are protected by copyright, with all rights reserved, unless otherwise indicated.