Evolution of NACA23012 wake vortices structure using PIV

The formation and development of a wing‐tip vortex in a near and extended near field were studied experimentally. A swept‐back tapered wing with a NACA23012 cross‐section was used as a vortex generator. Particle image velocimetry as a whole field velocity measurement technique was used in a low‐spee...

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Main Authors:	Elsayed, Omer Ali, Asrar, Waqar, Omar, Ashraf Ali, Kwon, Kijung
Format:	Article
Language:	English
Published:	American Society of Civil Engineers (ASCE) 2012
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/2105/ http://irep.iium.edu.my/2105/ http://irep.iium.edu.my/2105/ http://irep.iium.edu.my/2105/1/Evolution_of_NACA23012_Wake_Vortices_Structure_Using_PIV.pdf

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recordtype	eprints
spelling	iium-21052012-11-12T03:44:09Z http://irep.iium.edu.my/2105/ Evolution of NACA23012 wake vortices structure using PIV Elsayed, Omer Ali Asrar, Waqar Omar, Ashraf Ali Kwon, Kijung TL500 Aeronautics The formation and development of a wing‐tip vortex in a near and extended near field were studied experimentally. A swept‐back tapered wing with a NACA23012 cross‐section was used as a vortex generator. Particle image velocimetry as a whole field velocity measurement technique was used in a low‐speed wind tunnel to measure and characterize the wing tip vortex. Wake structures at successive downstream planes crosswise to the axis of the wake vortices were evaluated in terms of internal and external core radius, maximum tangential velocities, vorticity and circulation distributions. The effect of angle of attack on vortex parameters was examined at one downstream location. Internal core radius and circulation distributions were nearly constant along the downstream direction. A direct dependence of the circulation and tangential velocity distribution on the angle of attack was evident. The centers of the wing tip vortices scatter in a circle of radius nearly equal to 1% of the mean wing chord. Meandering amplitudes showed no direct dependence on the vortex strength but increase along the downstream direction. Good agreement was obtained between the theoretical exponential vortex model and the measured data. Computed induced rolling moment coefficients generated by the wing are within the full roll control capability of a follower aircraft. American Society of Civil Engineers (ASCE) 2012-01 Article PeerReviewed application/pdf en http://irep.iium.edu.my/2105/1/Evolution_of_NACA23012_Wake_Vortices_Structure_Using_PIV.pdf Elsayed, Omer Ali and Asrar, Waqar and Omar, Ashraf Ali and Kwon, Kijung (2012) Evolution of NACA23012 wake vortices structure using PIV. Journal of Aerospace Engineering , 25 (1). pp. 10-20. ISSN 1943-5525 (O), 0893-1321 (P), http://ascelibrary.org/action/showAbstract?page=10&volume=25&issue=1&journalCode=jaeeez 10.1061/(ASCE)AS.1943-5525.0000109
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL500 Aeronautics
spellingShingle	TL500 Aeronautics Elsayed, Omer Ali Asrar, Waqar Omar, Ashraf Ali Kwon, Kijung Evolution of NACA23012 wake vortices structure using PIV
description	The formation and development of a wing‐tip vortex in a near and extended near field were studied experimentally. A swept‐back tapered wing with a NACA23012 cross‐section was used as a vortex generator. Particle image velocimetry as a whole field velocity measurement technique was used in a low‐speed wind tunnel to measure and characterize the wing tip vortex. Wake structures at successive downstream planes crosswise to the axis of the wake vortices were evaluated in terms of internal and external core radius, maximum tangential velocities, vorticity and circulation distributions. The effect of angle of attack on vortex parameters was examined at one downstream location. Internal core radius and circulation distributions were nearly constant along the downstream direction. A direct dependence of the circulation and tangential velocity distribution on the angle of attack was evident. The centers of the wing tip vortices scatter in a circle of radius nearly equal to 1% of the mean wing chord. Meandering amplitudes showed no direct dependence on the vortex strength but increase along the downstream direction. Good agreement was obtained between the theoretical exponential vortex model and the measured data. Computed induced rolling moment coefficients generated by the wing are within the full roll control capability of a follower aircraft.
format	Article
author	Elsayed, Omer Ali Asrar, Waqar Omar, Ashraf Ali Kwon, Kijung
author_facet	Elsayed, Omer Ali Asrar, Waqar Omar, Ashraf Ali Kwon, Kijung
author_sort	Elsayed, Omer Ali
title	Evolution of NACA23012 wake vortices structure using PIV
title_short	Evolution of NACA23012 wake vortices structure using PIV
title_full	Evolution of NACA23012 wake vortices structure using PIV
title_fullStr	Evolution of NACA23012 wake vortices structure using PIV
title_full_unstemmed	Evolution of NACA23012 wake vortices structure using PIV
title_sort	evolution of naca23012 wake vortices structure using piv
publisher	American Society of Civil Engineers (ASCE)
publishDate	2012
url	http://irep.iium.edu.my/2105/ http://irep.iium.edu.my/2105/ http://irep.iium.edu.my/2105/ http://irep.iium.edu.my/2105/1/Evolution_of_NACA23012_Wake_Vortices_Structure_Using_PIV.pdf
first_indexed	2023-09-18T20:09:38Z
last_indexed	2023-09-18T20:09:38Z
_version_	1777407390727012352

Evolution of NACA23012 wake vortices structure using PIV

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