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Fast response vanes for sensing flow patterns in helicopter rotor environmentWind tunnel experiments were conducted on four small-scale flow-direction vanes for the determination of aerodynamic response. The tests were further extended to include a standard sized low-inertia vane currently employed in aircraft flight testing. The four test vanes had different aspect ratios and were about 35 percent of the surface area of the standard vane. The test results indicate satisfactory damping and frequency response for all vanes tested and compare favorably with the standard design.
Document ID
19750006649
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Barna, P. S. (Old Dominion Univ. Norfolk, VA, United States)
Crossman, G. R. (Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-132545
Accession Number
75N14721
Funding Number(s)
CONTRACT_GRANT: NAS1-11707
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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