Unsteady flow over flexible wings at different low Reynolds numbers
In 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...
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Online Access: | http://dx.doi.org/10.1051/epjconf/201611402030 |
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doaj-2d20d6544ccd4bc7a89627be291232d32021-08-02T16:04:10ZengEDP SciencesEPJ Web of Conferences2100-014X2016-01-011140203010.1051/epjconf/201611402030epjconf_efm2016_02030Unsteady flow over flexible wings at different low Reynolds numbersGenç Mustafa Serdar0Özden Mustafa1Açikel Halil Hakan2Demir HacımuratIsabekov Iliasbek3Wind Engineering and Aerodynamic Research Group, Department of Energy Systems Engineering, Erciyes UniversityWind Engineering and Aerodynamic Research Group, Department of Energy Systems Engineering, Erciyes UniversityWind Engineering and Aerodynamic Research Group, Department of Energy Systems Engineering, Erciyes UniversityWind Engineering and Aerodynamic Research Group, Department of Energy Systems Engineering, Erciyes UniversityIn 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.http://dx.doi.org/10.1051/epjconf/201611402030 |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Genç Mustafa Serdar Özden Mustafa Açikel Halil Hakan Demir Hacımurat Isabekov Iliasbek |
spellingShingle |
Genç Mustafa Serdar Özden Mustafa Açikel Halil Hakan Demir Hacımurat Isabekov Iliasbek Unsteady flow over flexible wings at different low Reynolds numbers EPJ Web of Conferences |
author_facet |
Genç Mustafa Serdar Özden Mustafa Açikel Halil Hakan Demir Hacımurat Isabekov Iliasbek |
author_sort |
Genç Mustafa Serdar |
title |
Unsteady flow over flexible wings at different low Reynolds numbers |
title_short |
Unsteady flow over flexible wings at different low Reynolds numbers |
title_full |
Unsteady flow over flexible wings at different low Reynolds numbers |
title_fullStr |
Unsteady flow over flexible wings at different low Reynolds numbers |
title_full_unstemmed |
Unsteady flow over flexible wings at different low Reynolds numbers |
title_sort |
unsteady flow over flexible wings at different low reynolds numbers |
publisher |
EDP Sciences |
series |
EPJ Web of Conferences |
issn |
2100-014X |
publishDate |
2016-01-01 |
description |
In 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. |
url |
http://dx.doi.org/10.1051/epjconf/201611402030 |
work_keys_str_mv |
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