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Analytical and experimental investigation of mistuning in propfan flutterAn analytical and experimental investigation of the effects of mistuning on propfan subsonic flutter was performed. The analytical model is based on the normal modes of a rotating composite blade and a three-dimensinal subsonic unsteady lifting surface aerodynamic theory. Theoretical and experimental results are compared for selected cases at different blade pitch angles, rotational speeds, and free-stream Mach numbers. The comparison shows a reasonably good agreement between theory and experiment. Both theory and experiment showed that combined mode shape, frequency, and aerodynamic mistuning can have a beneficial or adverse effect on blade damping depending on Mach number. Additional parametric results showed that alternative blade frequency mistuning does not have enough potential for it to be used as a passive flutter control in propfans similar to the one studied. It can be inferred from the results that a laminated composite propfan blade can be tailored to optimize its flutter speed by selecting the proper ply angles.
Document ID
19870008683
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kaza, Krishna Rao V. (NASA Lewis Research Center Cleveland, OH, United States)
Mehmed, Oral (NASA Lewis Research Center Cleveland, OH, United States)
Williams, Marc (Purdue Univ. West Lafayette, Ind., United States)
Moss, Larry A. (Sverdrup Technology, Inc. Cleveland, Ohio, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1987
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TM-88959
E-3412
NAS 1.15:88959
AIAA PAPER 87-0739
Accession Number
87N18116
Funding Number(s)
PROJECT: RTOP 505-63-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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