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Force Measurements on a Reflex Cambered Delta Wing

Holla, VS and Aravamudhan, MD and Rao, P Jagadeesha (1982) Force Measurements on a Reflex Cambered Delta Wing. In: Journal of Aircraft, 19 (6). pp. 417-418.

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Official URL: http://www.aiaa.org/content.cfm?pageid=406&gTable=...

Abstract

AREFLEX spanwise cambered delta wing with a conical camber designed for M= 1.4, using the method of Ref. 1, was tested at the design Mach number as well as off-design Mach number M=0.15 and 2.3, respectively. The test results are compared with those of a plane wing and also with the available theoretical results at the design condition. At subsonic speed, the cambered wing has less lift at a given incidence and higher lift-to-drag ratio at a given lift than the plane wing, while at supersonic speeds, both of these quantities were less on the cambered wing. At supersonic speed, at the design incidence and Mach number, there is good agreement between results from theory and experiment. The center of pressure on the cambered wing is ahead of that on the plane wing at subsonic speed, while the reverse is true at supersonic speeds. Finally, it is found that over a useful range of lift the cambered wing is aerodynamically more efficient at subsonic speeds, and less so at supersonic speeds, than the plane wing.

Item Type: Journal Article
Additional Information: Copyright of this article belongs to American Institute of Aeronautics and Astronautics.
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)
Date Deposited: 22 Jul 2009 07:30
Last Modified: 22 Jul 2009 07:30
URI: http://eprints.iisc.ernet.in/id/eprint/21705

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