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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/6010/1/Infulence_of_differential__spoiler_settings_on_the_wake_vortex.pdf
http://irep.iium.edu.my/6010/
http://www1.aiaa.org/content.cfm?pageid=406&gTable=jaPaper&gid=51221
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spelling my.iium.irep.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 REM 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
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
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/6010/1/Infulence_of_differential__spoiler_settings_on_the_wake_vortex.pdf
http://irep.iium.edu.my/6010/
http://www1.aiaa.org/content.cfm?pageid=406&gTable=jaPaper&gid=51221
_version_ 1643605655995547648
score 13.211869

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