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Performance and loads data from a wind tunnel test of a full-scale, coaxial, hingeless rotor helicopterA full-scale XH-59A advancing blade concept helicopter was tested in Ames Research Center's 40 by 80 foot wind tunnel. The helicopter was tested with the rotor on and off, rotor hub fairings on and off, interrotor shaft fairing on and off, rotor instrumentation module on and off, and auxiliary propulsion thrust on and off. An advance ratio range of 0.25 and 0.45 with the rotor on and from 60 to 180 knots with the rotor off was investigated. Data on aerodynamic forces and moments, rotor loads, rotor control positions and vibration for the XH-59A as well as the aerodynamic performance of the isolated rotor are presented.
Document ID
19820004167
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Felker, F. F., III (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-81329
USAAVRADCOM-TR-81-A-27
A-8732
Accession Number
82N12040
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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