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.
A comparison of theory and experiment for aeroelastic stability of a hingeless rotor model in hover
1988-06-01
Conference paper
No indication
English
Aeroelastic Stability of Hingeless, Elastically Tailored Rotor Blades in Hover
British Library Online Contents | 1993
|Aeroelastic stability of hingeless rotor blade in hover using large deflection theory
Tema Archive | 1994
|Aeroelastic Stability of Hingeless Rotor Blade in Hover Using Large Deflection Theory
Online Contents | 1994
|