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A comparison of theory and experiment for aeroelastic stability of a hingeless rotor model in hover

Author
Sharpe, David L.
Published
Jun 1, 1988.
Physical Description
1 electronic document
Online Version

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Summary
Theoretical predictions of aeroelastic stability are compared with experimental, isolated, hingeless-rotor data. The six cases selected represent a torsionally soft rotor having either a stiff or soft pitch-control system in combination with zero precone and droop, 5 degree precone, or -5 degree droop. Analyses from Bell Helicopter Textron, Boeing Vertol, Hughes Helicopters, Sikorsky Aircraft, the National Aeronautics and Space Administration, and the U.S. Army Aeromechanics Laboratory were compared with the experimental data. The correlation ranged from poor to fair.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19880017766.
Accession ID: 88N27150.
NASA, Ames Research Center, Integrated Technology Rotor Methodology Assessment Workshop; p 7-23.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15694089