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An unsteady wake model for a hingeless rotorA simple nonsteady wake model derived from the unsteady moment of the momentum equation for zero advance ratio is correlated with cyclic pitch frequency response tests conducted with a small hingeless rotor model. Two and three or more bladed rotor analyses are presented.
Document ID
19740035390
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Crews, S. T.
Hohenemser, K. H. (Washington University St. Louis, Mo., United States)
Ormiston, R. A. (U.S. Army, Air Mobility Research and Development Laboratory, Moffett Field Calif., United States)
Date Acquired
August 7, 2013
Publication Date
December 1, 1973
Publication Information
Publication: Journal of Aircraft
Volume: 10
Subject Category
Aerodynamics
Accession Number
74A18140
Funding Number(s)
CONTRACT_GRANT: NAS2-4151
Distribution Limits
Public
Copyright
Other

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