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Leading edge vortex-flap experiments on a 74 deg delta wingExploratory wind tunnel tests are reported on a 74 deg. delta wing model. The potential of a vortex flap concept in reducing the subsonic lift dependent drag of highly swept, slender wings is examined. The suction effect of coiled vortices generated through controlled separation over leading edge flap surfaces to produce a thrust component is discussed. A series of vortex-flap configurations were investigated to explore the effect of some primary geometric variables.
Document ID
19800002792
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Rao, D. M. (Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-159161
Accession Number
80N11038
Funding Number(s)
CONTRACT_GRANT: NSG-1315
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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