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Wind-tunnel development of underwing leading-edge vortex generators on a NASA supercritical-wing research airplane configurationA program for the wind tunnel development of underwing leading-edge vortex generators on an NASA supercritical-wing research airplane model was conducted in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.25 to 0.99. The effects on the longitudinal aerodynamic characteristics of vortex-generator wing semispan location, distance from wing leading edge, leading-edge sweep angle, toe-in angle, and span are presented. The effects of the vortex generators on the lateral-directional aerodynamic characteristics of the model for a sideslip angle of 5 deg are included.
Document ID
19830002762
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Bartlett, D. W. (NASA Langley Research Center Hampton, VA, United States)
Harris, C. D. (NASA Langley Research Center Hampton, VA, United States)
Kelly, T. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1973
Subject Category
Aeronautics (General)
Report/Patent Number
NASA-TM-X-2808
NAS 1.15:X-2808
L-8495
Report Number: NASA-TM-X-2808
Report Number: NAS 1.15:X-2808
Report Number: L-8495
Accession Number
83N11032
Funding Number(s)
PROJECT: RTOP 767-73-01-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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