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Experimentally determined flutter from two- and three-bladed model bearingless rotors in hoverA series of experiments was performed on a 1.8-m-diam model rotor in hover for the principal purpose of investigating the lead-lag stability of isolated bearingless rotors. Incidental to those tests, at least three types of pitch-flap flutter were encountered. Type 1 flutter occurred approximately at the second flap-mode frequency on both two-and three-bladed rotors for both small and large pitch angles and appeared to be a classic pitch-flap flutter. Type 2 flutter showed mostly torsional motion and was seen on both two- and three-bladed rotors. Type 3 flutter was a regressing flap flutter that occurred for only the three-bladed rotor configurations and appears to be a wake excited flutter. Although flutter occurred on a number of different configurations, no rotor parameters were identified that were clearly stabilizing or destabilizing.
Document ID
19860005816
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bousman, W. G. (Army Aviation Systems Command Moffett Field, CA, United States)
Dawson, S. (Army Aviation Systems Command Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
November 1, 1985
Publication Information
Publication: NASA. Ames Research Center Rotorcraft Dynamics 1984
Subject Category
Aircraft Stability And Control
Accession Number
86N15286
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19860005810Collected WorksRotorcraft Dynamics 1984
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