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Effect of steady state coning angle and damping on whirl flutter stabilityThe main object of this investigation is to find the effect of the steady state coning angle and the damping at the flapping hinge of the blades on the whirl flutter stability boundary and thus to determine the role they can play in narrowing down the gap between theory and experiment. The governing equations of motion, with these two parameters included are derived by the classical Lagrangian approach using quasi-steady blade element theory for aerodynamic forces. A linearized analysis of these equations is applied to two of the wind tunnel models of the previous investigations. The results indicate that these parameters have a marked effect on stability boundary and they may even change the mode of flutter from backward whirl to forward whirl.
Document ID
19740033217
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Kaza, K. R. V.
(Stanford University Stanford, Calif., United States)
Date Acquired
August 7, 2013
Publication Date
November 1, 1973
Publication Information
Publication: Journal of Aircraft
Volume: 10
Subject Category
Structural Mechanics
Accession Number
74A15967
Funding Number(s)
CONTRACT_GRANT: NGL-05-020-243
Distribution Limits
Public
Copyright
Other

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