Impact of a reverse delta type add-on device on the flap-tip vortex of a wing

The effect of interactions of vortices produced by an outboard flap-tip of a half-span wing (NACA 23012 in landing configuration) and a slender reverse delta type add-on device, placed in the proximity of the outboard flap-tip, on the upper surface of the half-span wing is investigated using Particl...

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Main Authors:	Altaf, Afaq, Tan, Boon Thong, Omar, Ashraf Ali, Asrar, Waqar
Format:	Article
Language:	English English
Published:	2016
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/51977/ http://irep.iium.edu.my/51977/ http://irep.iium.edu.my/51977/1/Impact%20of%20a%20Reverse%20Delta%20Type%20Add-on%20Device%20on%20the%20Flap-tip%20Vortex%20of%20a%20Wing.pdf http://irep.iium.edu.my/51977/7/51977_Impact%20of%20a%20reverse%20delta%20type%20add-on%20device%20_SCOPUS.pdf

id	iium-51977
recordtype	eprints
spelling	iium-519772017-07-04T07:28:25Z http://irep.iium.edu.my/51977/ Impact of a reverse delta type add-on device on the flap-tip vortex of a wing Altaf, Afaq Tan, Boon Thong Omar, Ashraf Ali Asrar, Waqar TL500 Aeronautics The effect of interactions of vortices produced by an outboard flap-tip of a half-span wing (NACA 23012 in landing configuration) and a slender reverse delta type add-on device, placed in the proximity of the outboard flap-tip, on the upper surface of the half-span wing is investigated using Particle Image Velocimetry in a closed loop low speed wind tunnel. Specifically the characteristics of the vortex interactions generated downstream in planes perpendicular to the free stream direction and their dependence on angles of attack at a chord-based Reynolds number of Rec=2.75×105 have been determined. It was found that the add-on device significantly reduces the tangential velocity magnitude and enlarges the vortex core of the resultant vortex by up to 36%. The aerodynamic performance of the half-span wing model was marginally affected by the use of a reverse delta type add-on device. The reduction in lift coefficient is 3.8% and the increase in drag coefficient is 14.9%. 2016 Article PeerReviewed application/pdf en http://irep.iium.edu.my/51977/1/Impact%20of%20a%20Reverse%20Delta%20Type%20Add-on%20Device%20on%20the%20Flap-tip%20Vortex%20of%20a%20Wing.pdf application/pdf en http://irep.iium.edu.my/51977/7/51977_Impact%20of%20a%20reverse%20delta%20type%20add-on%20device%20_SCOPUS.pdf Altaf, Afaq and Tan, Boon Thong and Omar, Ashraf Ali and Asrar, Waqar (2016) Impact of a reverse delta type add-on device on the flap-tip vortex of a wing. International Journal of Aviation, Aeronautics, and Aerospace, 3 (3). pp. 1-28. E-ISSN 2374-6793 http://commons.erau.edu/ijaaa/vol3/iss3/12/
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TL500 Aeronautics
spellingShingle	TL500 Aeronautics Altaf, Afaq Tan, Boon Thong Omar, Ashraf Ali Asrar, Waqar Impact of a reverse delta type add-on device on the flap-tip vortex of a wing
description	The effect of interactions of vortices produced by an outboard flap-tip of a half-span wing (NACA 23012 in landing configuration) and a slender reverse delta type add-on device, placed in the proximity of the outboard flap-tip, on the upper surface of the half-span wing is investigated using Particle Image Velocimetry in a closed loop low speed wind tunnel. Specifically the characteristics of the vortex interactions generated downstream in planes perpendicular to the free stream direction and their dependence on angles of attack at a chord-based Reynolds number of Rec=2.75×105 have been determined. It was found that the add-on device significantly reduces the tangential velocity magnitude and enlarges the vortex core of the resultant vortex by up to 36%. The aerodynamic performance of the half-span wing model was marginally affected by the use of a reverse delta type add-on device. The reduction in lift coefficient is 3.8% and the increase in drag coefficient is 14.9%.
format	Article
author	Altaf, Afaq Tan, Boon Thong Omar, Ashraf Ali Asrar, Waqar
author_facet	Altaf, Afaq Tan, Boon Thong Omar, Ashraf Ali Asrar, Waqar
author_sort	Altaf, Afaq
title	Impact of a reverse delta type add-on device on the flap-tip vortex of a wing
title_short	Impact of a reverse delta type add-on device on the flap-tip vortex of a wing
title_full	Impact of a reverse delta type add-on device on the flap-tip vortex of a wing
title_fullStr	Impact of a reverse delta type add-on device on the flap-tip vortex of a wing
title_full_unstemmed	Impact of a reverse delta type add-on device on the flap-tip vortex of a wing
title_sort	impact of a reverse delta type add-on device on the flap-tip vortex of a wing
publishDate	2016
url	http://irep.iium.edu.my/51977/ http://irep.iium.edu.my/51977/ http://irep.iium.edu.my/51977/1/Impact%20of%20a%20Reverse%20Delta%20Type%20Add-on%20Device%20on%20the%20Flap-tip%20Vortex%20of%20a%20Wing.pdf http://irep.iium.edu.my/51977/7/51977_Impact%20of%20a%20reverse%20delta%20type%20add-on%20device%20_SCOPUS.pdf
first_indexed	2023-09-18T21:13:42Z
last_indexed	2023-09-18T21:13:42Z
_version_	1777411421281189888

Impact of a reverse delta type add-on device on the flap-tip vortex of a wing

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