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Some steady and oscillating airfoil test results, including the effects of sweep, from the tunnel spanning wingA large scale tunnel spanning wing was built and tested. The model can be operated as either a swept or unswept wing and can be tested in steady state or oscillated sinusoidally in pitch about its quarter chord. Data is taken at mid-span with an internal 6-component balance and is also obtained from miniature pressure transducers distributed near the center span region. A description is given of the system and a brief discussion of some of the steady and unsteady results obtained to date. These are the steady load behavior to Mach numbers of approximately 1.1 and unsteady loads, including drag, at a reduced frequency of approximately 0.1.
Document ID
19790011888
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Carta, F. O. (United Technologies Research Center East Hartford, CT, United States)
St.hilaire, A. O. (United Technologies Research Center East Hartford, CT, United States)
Rorke, J. B. (United Technologies Corp.)
Jepson, W. D. (United Technologies Corp.)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Publication Information
Publication: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 1
Subject Category
Aerodynamics
Accession Number
79N20059
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19790011859Collected WorksAdvanced Technology Airfoil Research, volume 1, part 1
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