Study of the reverse delta wing

Particle image velocimetry was used in a low-speed wind tunnel to investigate the vortex structures of a slender reverse delta wing at various angles of attack and roll. This work investigates the characteristics of the vortices generated downstream in planes perpendicular to the freestream direct...

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Bibliographic Details
Main Authors:	Altaf, Afaq, Omar, Ashraf Ali E., Asrar, Waqar
Format:	Article
Language:	English
Published:	American Institute of Aeronautical and Astronautic 2011
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/2065/ http://irep.iium.edu.my/2065/ http://irep.iium.edu.my/2065/ http://irep.iium.edu.my/2065/1/Study_of_the_Reverse_Delta_Wing.pdf

id	iium-2065
recordtype	eprints
spelling	iium-20652011-11-23T08:10:24Z http://irep.iium.edu.my/2065/ Study of the reverse delta wing Altaf, Afaq Omar, Ashraf Ali E. Asrar, Waqar TL500 Aeronautics Particle image velocimetry was used in a low-speed wind tunnel to investigate the vortex structures of a slender reverse delta wing at various angles of attack and roll. This work investigates the characteristics of the vortices generated downstream in planes perpendicular to the freestream direction and their dependence on angles of attack and roll at a chord-based Reynolds number of Rec= 382000 The peak tangential velocities at�angle of attack higher than 5 deg show a trend similar to a delta wing. A six-component balance was used to obtain the aerodynamic coefficients for a reverse delta wing as well as a delta wing for comparison. A simulation of the streamlines, velocity vectors, and surface pressure contours was carried out using computational fluid dynamics software to show the characteristics of the flow over a reverse delta wing. American Institute of Aeronautical and Astronautic 2011-01 Article PeerReviewed application/pdf en http://irep.iium.edu.my/2065/1/Study_of_the_Reverse_Delta_Wing.pdf Altaf, Afaq and Omar, Ashraf Ali E. and Asrar, Waqar (2011) Study of the reverse delta wing. Journal of Aircraft, 48 (1). pp. 277-286. ISSN 0021-8669 http://www.aiaa.org/content.cfm?pageid=318 10.2514/1.C031101
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 Altaf, Afaq Omar, Ashraf Ali E. Asrar, Waqar Study of the reverse delta wing
description	Particle image velocimetry was used in a low-speed wind tunnel to investigate the vortex structures of a slender reverse delta wing at various angles of attack and roll. This work investigates the characteristics of the vortices generated downstream in planes perpendicular to the freestream direction and their dependence on angles of attack and roll at a chord-based Reynolds number of Rec= 382000 The peak tangential velocities at�angle of attack higher than 5 deg show a trend similar to a delta wing. A six-component balance was used to obtain the aerodynamic coefficients for a reverse delta wing as well as a delta wing for comparison. A simulation of the streamlines, velocity vectors, and surface pressure contours was carried out using computational fluid dynamics software to show the characteristics of the flow over a reverse delta wing.
format	Article
author	Altaf, Afaq Omar, Ashraf Ali E. Asrar, Waqar
author_facet	Altaf, Afaq Omar, Ashraf Ali E. Asrar, Waqar
author_sort	Altaf, Afaq
title	Study of the reverse delta wing
title_short	Study of the reverse delta wing
title_full	Study of the reverse delta wing
title_fullStr	Study of the reverse delta wing
title_full_unstemmed	Study of the reverse delta wing
title_sort	study of the reverse delta wing
publisher	American Institute of Aeronautical and Astronautic
publishDate	2011
url	http://irep.iium.edu.my/2065/ http://irep.iium.edu.my/2065/ http://irep.iium.edu.my/2065/ http://irep.iium.edu.my/2065/1/Study_of_the_Reverse_Delta_Wing.pdf
first_indexed	2023-09-18T20:09:36Z
last_indexed	2023-09-18T20:09:36Z
_version_	1777407388845867008

Study of the reverse delta wing

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