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Induced rolling moment for NACA4412 plain and flapped wing

Elsayed, Omer Ali and Kwon, Kijung and Asrar, Waqar and Omar, Ashraf Ali E. (2010) Induced rolling moment for NACA4412 plain and flapped wing. International Journal of Aircraft Engineering and Aerospace Technology, 82 (1). pp. 23-32. ISSN 0002-2667

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Abstract

Purpose – The paper aims to compute rolling moments on a follower aircraft wing due to vortices generated by a plain and flapped NACA4412 wing using experimental particle image velocimetery (PIV) data. Design/methodology/approach – This paper describes the detailed variation of the induced rolling moment on a follower aircraft wing derived from a PIV velocity field measurement. A rectangular wing of a subsonic wall interference model is used as a vortex generator in two different configurations: plain wing of NACA4412 cross-section profile; and flapped wing with trailing edge flap of NACA0012 cross-section profile extended at 20°. Findings – Results obtained showed that the maximum induced rolling moment coefficient depends on the strength of the vortex produced by the generating aircraft wing and increases linearly with the increment of the angle of attack. Originality/value – This paper provides an insight on the effects of different angles of attacks for plain and flapped wings on the induced rolling moment coefficient and therefore, the hazard imposed on the following aircraft can be estimated.

Item Type: Article (Journal)
Additional Information: 4277/1969
Uncontrolled Keywords: swing-wing aircraft, flight operations, flight dynamics, vortices
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500 Aeronautics
Kulliyyahs/Centres/Divisions/Institutes: Kulliyyah of Engineering
Kulliyyah of Engineering > Department of Mechanical Engineering
Depositing User: Prof. Ashraf Omar
Date Deposited: 13 Sep 2011 09:52
Last Modified: 14 Nov 2011 13:27
URI: http://irep.iium.edu.my/id/eprint/1969

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