Unsteady flow over flexible wings at different low Reynolds numbers

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dc.authoridDemir, Hacimurat -- 0000-0002-4819-2633; GENC, Mustafa Serdar -- 0000-0002-6540-620X
dc.contributor.authorGenç, Mustafa Serdar
dc.contributor.authorÖzden, Mustafa
dc.contributor.authorAçıkel, Halil Hakan
dc.contributor.authorDemir, Hacımurat
dc.contributor.authorIsabekov, Iliasbek
dc.contributor.editorDancova, P
dc.contributor.editorVesely, M
dc.date.accessioned13.07.201910:50:10
dc.date.accessioned2019-07-16T09:18:41Z
dc.date.available13.07.201910:50:10
dc.date.available2019-07-16T09:18:41Z
dc.date.issued2016
dc.departmentMühendislik Fakültesi
dc.description10th Anniversary International Conference on Experimental Fluid Mechanics -- NOV 17-20, 2015 -- Prague, CZECH REPUBLIC
dc.descriptionWOS:000400395300032
dc.description.abstractIn this study, unsteady flow around flexible membrane wing which had aspect ratio of 1 (AR=1) was investigated experimentally at various Reynolds numbers (Re = 25000 and Re = 50000). Smoke-wire technique for flow visualization over the flexible membrane wing was utilized in the experiments. Digital Image Correlation system (DIC) was used for measuring deformation of AR = 1 flexible membrane wing. Instantaneous deformation measurements of membrane wing were combined with the flow field measurements. In low aspect ratio flexible membrane wings, unsteadiness includes tip vortices and vortex shedding, and the combination of tip vortices. In these types of wings, complex unsteady deformations occurred due to vortex shedding. The results showed that the increasing angle of attack results in increase of membrane deformation. Moreover, it was concluded that analysis of the instantaneous deformation revealed chordwise and spanwise, modes which were due to the shedding of leading-edge vortices as well as tip vortices. Consequently, vibrational mode decreased and maximum standard deviation location approached to the trailing edge by reason of increasing angle of attack.
dc.description.sponsorshipDANTEC Dynam GmbH, LAVISION, LENAM, MECAS ESI s r o, MIT s r o, TSI GmbH
dc.description.sponsorshipScientific and Technological Research Council of Turkey (TUBITAK) [213M329]; Scientific Research Projects Unit of Erciyes University [FDK-2015-6171, FBG-2014-5337, FDA-2014-5273]
dc.description.sponsorshipThe authors would like to acknowledge funding from the Scientific and Technological Research Council of Turkey (TUBITAK) under the project no: 213M329, the Scientific Research Projects Unit of Erciyes University under the contract no: FDK-2015-6171, FBG-2014-5337 and FDA-2014-5273.
dc.identifier.doi10.1051/epjconf/201611402030
dc.identifier.issn2100-014X
dc.identifier.scopusqualityN/A
dc.identifier.urihttps://doi.org/10.1051/epjconf/201611402030
dc.identifier.urihttps://hdl.handle.net/20.500.12451/4907
dc.identifier.volume114en_US
dc.identifier.wosWOS:000400395300032
dc.identifier.wosqualityN/A
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherE D P Sciences
dc.relation.ispartofEFM15 - EXPERIMENTAL FLUID MECHANICS 2015
dc.relation.ispartofseriesEPJ Web of Conferences
dc.relation.publicationcategoryKonferans Öğesi - Uluslararası - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/openAccess
dc.titleUnsteady flow over flexible wings at different low Reynolds numbers
dc.typeConference Object

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