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Inflow measurement made with a laser velocimeter on a helicopter model in forward flight. Volume 3: Rectangular planform blades at an advance ratio of 0.30An experimental investigation was conducted in the 14- by 22-Foot Subsonic Tunnel at NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (micron sub infinity = 0.30). The measurements were made with a two component Laser Velocimeter (LV) one chord above the plane formed by the path of the rotor tips (tip path plane). A conditional sampling technique was employed to determine the azimuthal position of the rotor at the time that each velocity measurement was made so that the azimuthal fluctuations in velocity could be determined. Measurements were made at a total of 180 separate locations in order to clearly define the inflow character. These data are presented without analysis.
Document ID
19880012631
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Elliott, Joe W. (NASA Langley Research Center Hampton, VA., United States)
Althoff, Susan L. (NASA Langley Research Center Hampton, VA., United States)
Sailey, Richard H. (PRC Kentron, Inc. Hampton, Va., United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:100543
AVSCOM-TM-88-B-006
NASA-TM-100543
Accession Number
88N22015
Funding Number(s)
PROJECT: RTOP 505-61-51-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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