Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation

Experimental investigations using particle image velocimetry technique have been carried out for the evaluation of the differential spoiler setting capabilities in modifying the spanwise wing load and further reduce the wake vortex hazard. The aircraft half model (at high lift configuration) was inv...

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Main Authors:	Elsayed, Omer Ali, Asrar, Waqar, Omar, Ashraf Ali, Kwon, Kijung
Format:	Article
Language:	English
Published:	American Institute of Aeronautical and Astronautic 2010
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/6010/ http://irep.iium.edu.my/6010/ http://irep.iium.edu.my/6010/ http://irep.iium.edu.my/6010/1/Infulence_of_differential__spoiler_settings_on_the_wake_vortex.pdf

id	iium-6010
recordtype	eprints
spelling	iium-60102012-04-16T06:07:34Z http://irep.iium.edu.my/6010/ Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation Elsayed, Omer Ali Asrar, Waqar Omar, Ashraf Ali Kwon, Kijung TL500 Aeronautics Experimental investigations using particle image velocimetry technique have been carried out for the evaluation of the differential spoiler setting capabilities in modifying the spanwise wing load and further reduce the wake vortex hazard. The aircraft half model (at high lift configuration) was investigated for two differential spoiler settings. Results reveal a noticeable inboard shift of spanwise wing loading. Implementation of a differential spoiler setting results in a substantial redistribution of the flap tip vortex circulation with an increase in the diameter of the merged vortex by a factor of up to 2.72 relative to the undisturbed flap tip vortex. Inspection of the cross-stream distribution of axial vorticity shows a reduction by a factor of up to 2.33 in the peak vorticity value. A 44% decrease of the maximum crossflow velocity relative to the undisturbed flap tip vortex crossflow velocity was recorded for the case of deployed spoilers. Finally assessment of the differential spoiler setting capabilities as a wake vortex attenuation device reveals that, while position of the maximum induced rolling moments in the flap tip area is little influenced by the differential spoiler setting, the maximum induced rolling moment coefficient was reduced to nearly one third of the undisturbed flap tip vortex value. American Institute of Aeronautical and Astronautic 2010-09 Article PeerReviewed application/pdf en http://irep.iium.edu.my/6010/1/Infulence_of_differential__spoiler_settings_on_the_wake_vortex.pdf Elsayed, Omer Ali and Asrar, Waqar and Omar, Ashraf Ali and Kwon, Kijung (2010) Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation. Journal of Aircraft, 47 (5). pp. 1728-1738. ISSN 0021-8669 http://www1.aiaa.org/content.cfm?pageid=406&gTable=jaPaper&gid=51221 10.2514/1.51221
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 Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation
description	Experimental investigations using particle image velocimetry technique have been carried out for the evaluation of the differential spoiler setting capabilities in modifying the spanwise wing load and further reduce the wake vortex hazard. The aircraft half model (at high lift configuration) was investigated for two differential spoiler settings. Results reveal a noticeable inboard shift of spanwise wing loading. Implementation of a differential spoiler setting results in a substantial redistribution of the flap tip vortex circulation with an increase in the diameter of the merged vortex by a factor of up to 2.72 relative to the undisturbed flap tip vortex. Inspection of the cross-stream distribution of axial vorticity shows a reduction by a factor of up to 2.33 in the peak vorticity value. A 44% decrease of the maximum crossflow velocity relative to the undisturbed flap tip vortex crossflow velocity was recorded for the case of deployed spoilers. Finally assessment of the differential spoiler setting capabilities as a wake vortex attenuation device reveals that, while position of the maximum induced rolling moments in the flap tip area is little influenced by the differential spoiler setting, the maximum induced rolling moment coefficient was reduced to nearly one third of the undisturbed flap tip vortex value.
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	Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation
title_short	Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation
title_full	Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation
title_fullStr	Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation
title_full_unstemmed	Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation
title_sort	inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation
publisher	American Institute of Aeronautical and Astronautic
publishDate	2010
url	http://irep.iium.edu.my/6010/ http://irep.iium.edu.my/6010/ http://irep.iium.edu.my/6010/ http://irep.iium.edu.my/6010/1/Infulence_of_differential__spoiler_settings_on_the_wake_vortex.pdf
first_indexed	2023-09-18T20:14:50Z
last_indexed	2023-09-18T20:14:50Z
_version_	1777407717859655680

Inﬂuence of differential spoiler settings on the wake vortex characterization and alleviation

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