Experimental and computational analysis of stall cells on rectangular wings

Manolesos, Marinos; Papadakis, Georgios; Voutsinas, Spyros G.

doi:10.1002/we.1609

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Experimental and computational analysis of stall cells on rectangular wings

Marinos Manolesos

, Georgios Papadakis, Spyros G. Voutsinas

Wind Energy, Volume: 17, Issue: 6, Pages: 939 - 955

Swansea University Author: Marinos Manolesos

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DOI (Published version): 10.1002/we.1609

Abstract

The present paper is the second part of a combined (experimental and computational) study on stall cells (SCs) on a rectangular wing. In the first part, tuft data were used in order to geometrically characterize a stabilized SC resulting from a localized spanwise disturbance introduced by a zigzag t...

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Published in:	Wind Energy
ISSN:	1095-4244
Published:	2014
Online Access:	Check full text
URI:	https://cronfa.swan.ac.uk/Record/cronfa38904

first_indexed	2018-02-28T19:50:49Z
last_indexed	2019-09-18T19:57:04Z
id	cronfa38904
recordtype	SURis
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spelling	2019-09-18T16:51:25.1997166 v2 38904 2018-02-28 Experimental and computational analysis of stall cells on rectangular wings 44a3e0d351ccd7a8365d5fc7c50c8778 0000-0002-5506-6061 Marinos Manolesos Marinos Manolesos true false 2018-02-28 ACEM The present paper is the second part of a combined (experimental and computational) study on stall cells (SCs) on a rectangular wing. In the first part, tuft data were used in order to geometrically characterize a stabilized SC resulting from a localized spanwise disturbance introduced by a zigzag tape. Here, pressure measurements on the model and in the wake and aerodynamic polars at midspan are reported. The wing model had an aspect ratio value of 2, the Reynolds number was 106 and the range of angles of attack (α) was from −6° to 16°. Experimental results confirm previous findings. Furthermore, two‐dimensional and three‐dimensional Reynolds Averaged Navier‐Stokes RANS simulations are used in order to better understand the structure of SCs. 3D simulations reproduce the experimental data with a 3° delay in α and permit a qualitative analysis. It is found that the SC vortices start normal to the wing surface and extend downstream in the wake; the evolution of the SC vortices in the wake is in strong interaction with the separation line vortex and the trailing edge line vortex; as the SC vortex develops downstream in the wake, its centreline is contracted towards the SC centre; the wing wake is pushed upstream at the centre of the SC and downstream at the sides by the SC vortices; spanwise lift and drag distributions always attain their minimum at the SC centre. Journal Article Wind Energy 17 6 939 955 1095-4244 30 6 2014 2014-06-30 10.1002/we.1609 COLLEGE NANME Aerospace, Civil, Electrical, and Mechanical Engineering COLLEGE CODE ACEM Swansea University 2019-09-18T16:51:25.1997166 2018-02-28T18:10:04.5127684 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised Marinos Manolesos 0000-0002-5506-6061 1 Georgios Papadakis 2 Spyros G. Voutsinas 3 0038904-30042018093352.pdf manolesos2013.pdf 2018-04-30T09:33:52.2530000 Output 2169259 application/pdf Accepted Manuscript true 2018-04-30T00:00:00.0000000 false eng
title	Experimental and computational analysis of stall cells on rectangular wings
spellingShingle	Experimental and computational analysis of stall cells on rectangular wings Marinos Manolesos
title_short	Experimental and computational analysis of stall cells on rectangular wings
title_full	Experimental and computational analysis of stall cells on rectangular wings
title_fullStr	Experimental and computational analysis of stall cells on rectangular wings
title_full_unstemmed	Experimental and computational analysis of stall cells on rectangular wings
title_sort	Experimental and computational analysis of stall cells on rectangular wings
author_id_str_mv	44a3e0d351ccd7a8365d5fc7c50c8778
author_id_fullname_str_mv	44a3e0d351ccd7a8365d5fc7c50c8778_***_Marinos Manolesos
author	Marinos Manolesos
author2	Marinos Manolesos Georgios Papadakis Spyros G. Voutsinas
format	Journal article
container_title	Wind Energy
container_volume	17
container_issue	6
container_start_page	939
publishDate	2014
institution	Swansea University
issn	1095-4244
doi_str_mv	10.1002/we.1609
college_str	Faculty of Science and Engineering
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description	The present paper is the second part of a combined (experimental and computational) study on stall cells (SCs) on a rectangular wing. In the first part, tuft data were used in order to geometrically characterize a stabilized SC resulting from a localized spanwise disturbance introduced by a zigzag tape. Here, pressure measurements on the model and in the wake and aerodynamic polars at midspan are reported. The wing model had an aspect ratio value of 2, the Reynolds number was 106 and the range of angles of attack (α) was from −6° to 16°. Experimental results confirm previous findings. Furthermore, two‐dimensional and three‐dimensional Reynolds Averaged Navier‐Stokes RANS simulations are used in order to better understand the structure of SCs. 3D simulations reproduce the experimental data with a 3° delay in α and permit a qualitative analysis. It is found that the SC vortices start normal to the wing surface and extend downstream in the wake; the evolution of the SC vortices in the wake is in strong interaction with the separation line vortex and the trailing edge line vortex; as the SC vortex develops downstream in the wake, its centreline is contracted towards the SC centre; the wing wake is pushed upstream at the centre of the SC and downstream at the sides by the SC vortices; spanwise lift and drag distributions always attain their minimum at the SC centre.
published_date	2014-06-30T07:19:43Z
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score	11.04735

Experimental and computational analysis of stall cells on rectangular wings

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