No Cover Image

Journal article 943 views 195 downloads

Study of a stall cell using stereo particle image velocimetry

Marinos Manolesos, Spyros G. Voutsinas

Physics of Fluids, Volume: 26, Issue: 4

Swansea University Author: Marinos Manolesos

Check full text

DOI (Published version): 10.1063/1.4869726

Abstract

The structure of Stall Cells (SCs) on wings is analyzed on the basis of stereo particle image velocimetry measurements. All experiments regard a Reynolds number 0.87 × 106 flow around a rectangular wing with endplates and an aspect ratio of 2.0. The inherently unstable stall cell is stabilized by me...

Full description

Published in: Physics of Fluids
ISSN: 1070-6631 1089-7666
Published: 2014
Online Access: Check full text

URI: https://cronfa.swan.ac.uk/Record/cronfa38903
Tags: Add Tag
No Tags, Be the first to tag this record!
first_indexed 2018-02-28T19:50:49Z
last_indexed 2023-02-09T03:48:19Z
id cronfa38903
recordtype SURis
fullrecord <?xml version="1.0"?><rfc1807><datestamp>2023-02-08T17:28:32.5861530</datestamp><bib-version>v2</bib-version><id>38903</id><entry>2018-02-28</entry><title>Study of a stall cell using stereo particle image velocimetry</title><swanseaauthors><author><sid>44a3e0d351ccd7a8365d5fc7c50c8778</sid><firstname>Marinos</firstname><surname>Manolesos</surname><name>Marinos Manolesos</name><active>true</active><ethesisStudent>false</ethesisStudent></author></swanseaauthors><date>2018-02-28</date><deptcode>FGSEN</deptcode><abstract>The structure of Stall Cells (SCs) on wings is analyzed on the basis of stereo particle image velocimetry measurements. All experiments regard a Reynolds number 0.87 &#xD7; 106 flow around a rectangular wing with endplates and an aspect ratio of 2.0. The inherently unstable stall cell is stabilized by means of a localized spanwise disturbance. Velocity, vorticity, and Reynolds stress data above the wing and in the wake are presented and discussed, also in combination with Computational Fluid Dynamics data. The present study completes and clarifies the previously suggested models regarding the SC structure. The SC emerges in between the separation and trailing edge shear layer where three different types of vortices are identified: (a) the stall cell vortices that start normal to the wing surface and continue downstream aligned with the free stream, (b) the separation line vortex, and (c) the trailing edge line vortex that both run parallel to the wing trailing edge and grow significantly at the center of the stall cell. Analysis of the Reynolds stress data reveals high anisotropy. Concentration of high streamwise shear stress values is connected to the two shear layers and high cross shear Reynolds stresses are connected to vortex stretching. High normal Reynolds stress values are observed (a) in the separation but not in the trailing edge shear layer indicating the flapping of the former and (b) along the stall cell vortices indicating their wandering motion. The eddy viscosity based Reynolds averaged Navier-Stokes simulations are found in good qualitative agreement with the experiments in terms of the type and position of the identified vortex structures, an agreement which is linked to the correct trend in the predicted shear Reynolds stresses distributions. Quantitative deviations of the numerical results from the measurements are attributed to the isotropic definition of the turbulence model. Therefore, use of large eddy simulation is suggested for better prediction of the flow.</abstract><type>Journal Article</type><journal>Physics of Fluids</journal><volume>26</volume><journalNumber>4</journalNumber><paginationStart/><paginationEnd/><publisher/><placeOfPublication/><isbnPrint/><isbnElectronic/><issnPrint>1070-6631</issnPrint><issnElectronic>1089-7666</issnElectronic><keywords/><publishedDay>30</publishedDay><publishedMonth>4</publishedMonth><publishedYear>2014</publishedYear><publishedDate>2014-04-30</publishedDate><doi>10.1063/1.4869726</doi><url/><notes/><college>COLLEGE NANME</college><department>Science and Engineering - Faculty</department><CollegeCode>COLLEGE CODE</CollegeCode><DepartmentCode>FGSEN</DepartmentCode><institution>Swansea University</institution><apcterm/><funders/><projectreference/><lastEdited>2023-02-08T17:28:32.5861530</lastEdited><Created>2018-02-28T18:09:48.4911884</Created><path><level id="1">Faculty of Science and Engineering</level><level id="2">School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Mechanical Engineering</level></path><authors><author><firstname>Marinos</firstname><surname>Manolesos</surname><order>1</order></author><author><firstname>Spyros G.</firstname><surname>Voutsinas</surname><order>2</order></author></authors><documents><document><filename>0038903-30042018094807.pdf</filename><originalFilename>manolesos2014.pdf</originalFilename><uploaded>2018-04-30T09:48:07.8270000</uploaded><type>Output</type><contentLength>3499530</contentLength><contentType>application/pdf</contentType><version>Accepted Manuscript</version><cronfaStatus>true</cronfaStatus><embargoDate>2018-04-30T00:00:00.0000000</embargoDate><copyrightCorrect>false</copyrightCorrect><language>eng</language></document></documents><OutputDurs/></rfc1807>
spelling 2023-02-08T17:28:32.5861530 v2 38903 2018-02-28 Study of a stall cell using stereo particle image velocimetry 44a3e0d351ccd7a8365d5fc7c50c8778 Marinos Manolesos Marinos Manolesos true false 2018-02-28 FGSEN The structure of Stall Cells (SCs) on wings is analyzed on the basis of stereo particle image velocimetry measurements. All experiments regard a Reynolds number 0.87 × 106 flow around a rectangular wing with endplates and an aspect ratio of 2.0. The inherently unstable stall cell is stabilized by means of a localized spanwise disturbance. Velocity, vorticity, and Reynolds stress data above the wing and in the wake are presented and discussed, also in combination with Computational Fluid Dynamics data. The present study completes and clarifies the previously suggested models regarding the SC structure. The SC emerges in between the separation and trailing edge shear layer where three different types of vortices are identified: (a) the stall cell vortices that start normal to the wing surface and continue downstream aligned with the free stream, (b) the separation line vortex, and (c) the trailing edge line vortex that both run parallel to the wing trailing edge and grow significantly at the center of the stall cell. Analysis of the Reynolds stress data reveals high anisotropy. Concentration of high streamwise shear stress values is connected to the two shear layers and high cross shear Reynolds stresses are connected to vortex stretching. High normal Reynolds stress values are observed (a) in the separation but not in the trailing edge shear layer indicating the flapping of the former and (b) along the stall cell vortices indicating their wandering motion. The eddy viscosity based Reynolds averaged Navier-Stokes simulations are found in good qualitative agreement with the experiments in terms of the type and position of the identified vortex structures, an agreement which is linked to the correct trend in the predicted shear Reynolds stresses distributions. Quantitative deviations of the numerical results from the measurements are attributed to the isotropic definition of the turbulence model. Therefore, use of large eddy simulation is suggested for better prediction of the flow. Journal Article Physics of Fluids 26 4 1070-6631 1089-7666 30 4 2014 2014-04-30 10.1063/1.4869726 COLLEGE NANME Science and Engineering - Faculty COLLEGE CODE FGSEN Swansea University 2023-02-08T17:28:32.5861530 2018-02-28T18:09:48.4911884 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Mechanical Engineering Marinos Manolesos 1 Spyros G. Voutsinas 2 0038903-30042018094807.pdf manolesos2014.pdf 2018-04-30T09:48:07.8270000 Output 3499530 application/pdf Accepted Manuscript true 2018-04-30T00:00:00.0000000 false eng
title Study of a stall cell using stereo particle image velocimetry
spellingShingle Study of a stall cell using stereo particle image velocimetry
Marinos Manolesos
title_short Study of a stall cell using stereo particle image velocimetry
title_full Study of a stall cell using stereo particle image velocimetry
title_fullStr Study of a stall cell using stereo particle image velocimetry
title_full_unstemmed Study of a stall cell using stereo particle image velocimetry
title_sort Study of a stall cell using stereo particle image velocimetry
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 Physics of Fluids
container_volume 26
container_issue 4
publishDate 2014
institution Swansea University
issn 1070-6631
1089-7666
doi_str_mv 10.1063/1.4869726
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 Aerospace, Civil, Electrical, General and Mechanical Engineering - Mechanical Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Mechanical Engineering
document_store_str 1
active_str 0
description The structure of Stall Cells (SCs) on wings is analyzed on the basis of stereo particle image velocimetry measurements. All experiments regard a Reynolds number 0.87 × 106 flow around a rectangular wing with endplates and an aspect ratio of 2.0. The inherently unstable stall cell is stabilized by means of a localized spanwise disturbance. Velocity, vorticity, and Reynolds stress data above the wing and in the wake are presented and discussed, also in combination with Computational Fluid Dynamics data. The present study completes and clarifies the previously suggested models regarding the SC structure. The SC emerges in between the separation and trailing edge shear layer where three different types of vortices are identified: (a) the stall cell vortices that start normal to the wing surface and continue downstream aligned with the free stream, (b) the separation line vortex, and (c) the trailing edge line vortex that both run parallel to the wing trailing edge and grow significantly at the center of the stall cell. Analysis of the Reynolds stress data reveals high anisotropy. Concentration of high streamwise shear stress values is connected to the two shear layers and high cross shear Reynolds stresses are connected to vortex stretching. High normal Reynolds stress values are observed (a) in the separation but not in the trailing edge shear layer indicating the flapping of the former and (b) along the stall cell vortices indicating their wandering motion. The eddy viscosity based Reynolds averaged Navier-Stokes simulations are found in good qualitative agreement with the experiments in terms of the type and position of the identified vortex structures, an agreement which is linked to the correct trend in the predicted shear Reynolds stresses distributions. Quantitative deviations of the numerical results from the measurements are attributed to the isotropic definition of the turbulence model. Therefore, use of large eddy simulation is suggested for better prediction of the flow.
published_date 2014-04-30T03:49:21Z
_version_ 1763752397199376384
score 10.999252

Similar Items