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Development of an unsteady aerodynamics model to improve correlation of computed blade stresses with test dataA reliable rotor aeroelastic analysis operational that correctly predicts the vibration levels for a helicopter is utilized to test various unsteady aerodynamics models with the objective of improving the correlation between test and theory. This analysis called Rotor Aeroelastic Vibration (RAVIB) computer program is based on a frequency domain forced response analysis which utilizes the transfer matrix techniques to model helicopter/rotor dynamic systems of varying degrees of complexity. The results for the AH-1G helicopter rotor were compared with the flight test data during high speed operation and they indicated a reasonably good correlation for the beamwise and chordwise blade bending moments, but for torsional moments the correlation was poor. As a result, a new aerodynamics model based on unstalled synthesized data derived from the large amplitude oscillating airfoil experiments was developed and tested.
Document ID
19860005818
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gangwani, S. T.
(Hughes Helicopters Culver City, CA, United States)
Date Acquired
August 12, 2013
Publication Date
November 1, 1985
Publication Information
Publication: NASA. Ames Research Center Rotorcraft Dynamics 11984
Subject Category
Aerodynamics
Accession Number
86N15288
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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