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Experimental Study of Drag-Reduction Devices on a Flatback Airfoil

Marinos Manolesos, Spyros G. Voutsinas

AIAA Journal, Volume: 54, Issue: 11, Pages: 3382 - 3396

Swansea University Author: Marinos Manolesos

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DOI (Published version): 10.2514/1.j054901

Abstract

Various trailing-edge drag-reduction devices, including a new flap device, were examined experimentally on a flatback airfoil in a wind tunnel. The tests concerned a 30% thick airfoil with 10.6% thick trailing edge. Pressure, hot wire, and stereo particle image velocimetry measurements were performe...

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Published in: AIAA Journal
ISSN: 0001-1452 1533-385X
Published: American Institute of Aeronautics and Astronautics (AIAA) 2016
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URI: https://cronfa.swan.ac.uk/Record/cronfa38901
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first_indexed 2018-02-28T19:50:48Z
last_indexed 2020-07-13T18:58:14Z
id cronfa38901
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spelling 2020-07-13T15:41:43.9037640 v2 38901 2018-02-28 Experimental Study of Drag-Reduction Devices on a Flatback Airfoil 44a3e0d351ccd7a8365d5fc7c50c8778 Marinos Manolesos Marinos Manolesos true false 2018-02-28 FGSEN Various trailing-edge drag-reduction devices, including a new flap device, were examined experimentally on a flatback airfoil in a wind tunnel. The tests concerned a 30% thick airfoil with 10.6% thick trailing edge. Pressure, hot wire, and stereo particle image velocimetry measurements were performed at a chord Reynolds number of 1.5e6. Results show that the best-performing devices decrease drag, increase the vortex shedding frequency, and reduce flow variation downstream of the wing trailing edge. The best-performing device was a combination of the flap with an offset cavity plate. Further investigation is required for the optimization of the new device to examine its effects on noise reduction, load mitigation, and control. Journal Article AIAA Journal 54 11 3382 3396 American Institute of Aeronautics and Astronautics (AIAA) 0001-1452 1533-385X 30 11 2016 2016-11-30 10.2514/1.j054901 COLLEGE NANME Science and Engineering - Faculty COLLEGE CODE FGSEN Swansea University 2020-07-13T15:41:43.9037640 2018-02-28T18:08:08.4304222 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised Marinos Manolesos 1 Spyros G. Voutsinas 2 0038901-30042018094033.pdf manolesos2016.pdf 2018-04-30T09:40:33.3700000 Output 2565552 application/pdf Accepted Manuscript true 2018-04-30T00:00:00.0000000 true eng
title Experimental Study of Drag-Reduction Devices on a Flatback Airfoil
spellingShingle Experimental Study of Drag-Reduction Devices on a Flatback Airfoil
Marinos Manolesos
title_short Experimental Study of Drag-Reduction Devices on a Flatback Airfoil
title_full Experimental Study of Drag-Reduction Devices on a Flatback Airfoil
title_fullStr Experimental Study of Drag-Reduction Devices on a Flatback Airfoil
title_full_unstemmed Experimental Study of Drag-Reduction Devices on a Flatback Airfoil
title_sort Experimental Study of Drag-Reduction Devices on a Flatback Airfoil
author_id_str_mv 44a3e0d351ccd7a8365d5fc7c50c8778
author_id_fullname_str_mv 44a3e0d351ccd7a8365d5fc7c50c8778_***_Marinos Manolesos
author Marinos Manolesos
author2 Marinos Manolesos
Spyros G. Voutsinas
format Journal article
container_title AIAA Journal
container_volume 54
container_issue 11
container_start_page 3382
publishDate 2016
institution Swansea University
issn 0001-1452
1533-385X
doi_str_mv 10.2514/1.j054901
publisher American Institute of Aeronautics and Astronautics (AIAA)
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Engineering and Applied Sciences - Uncategorised{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Engineering and Applied Sciences - Uncategorised
document_store_str 1
active_str 0
description Various trailing-edge drag-reduction devices, including a new flap device, were examined experimentally on a flatback airfoil in a wind tunnel. The tests concerned a 30% thick airfoil with 10.6% thick trailing edge. Pressure, hot wire, and stereo particle image velocimetry measurements were performed at a chord Reynolds number of 1.5e6. Results show that the best-performing devices decrease drag, increase the vortex shedding frequency, and reduce flow variation downstream of the wing trailing edge. The best-performing device was a combination of the flap with an offset cavity plate. Further investigation is required for the optimization of the new device to examine its effects on noise reduction, load mitigation, and control.
published_date 2016-11-30T03:49:21Z
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score 10.999161

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