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Effects of wing leading-edge deflection on low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configurationStatic force tests were conducted in the Langley V/STOL tunnel at a Reynolds number (based on the mean aerodynamic chord) of about 2.0 x 10 to the 6th power for an angle-of-attack range from about - 10 deg to 17 deg and angles of sideslip of 0 and + or - 5 deg. Limited flow visualization studies were also conducted in order to provide a qualitative assessment of leading-edge upwash characteristics.
Document ID
19790017849
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Coe, P. L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Weston, R. P. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
L-12784
NASA-TP-1434
Accession Number
79N26020
Funding Number(s)
PROJECT: RTOP 517-53-43-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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