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An experimental study of the flow in a wing with a partial span drooped leading edgeThe flow field produced by a low aspect ratio wing (AR = 3.0) with a partial span leading edge droop was investigated in a series of low speed wind tunnel tests (Reynolds number based on 17.8 cm chord = 560,000). Photographs were obtained of surface oil flow patterns over an angle of attack range of alpha = 0 to 29 deg. Flow field surveys of the partially stalled wing at alpha = 25 deg were completed using a hot-wire probe, a split-film probe and a Conrad probe. The flow field survey data was presented using a color video display. The data indicated regions of apparent reversed flow in the separation region behind the wing and indicated the general cross-sectional shape of the separated wake flow.
Document ID
19820030861
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Winkelmann, A. E.
(Maryland Univ. College Park, MD, United States)
Tsao, C. P.
(Maryland, University College Park, MD, United States)
Date Acquired
August 10, 2013
Publication Date
August 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 81-1665
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Conference
Location: Dayton, OH
Start Date: August 11, 1981
End Date: August 13, 1981
Accession Number
82A14396
Funding Number(s)
CONTRACT_GRANT: NSG-1570
Distribution Limits
Public
Copyright
Other

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