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Supersonic axial-flow fan flutterLane's (1957) analytical formulation of the unsteady pressure distribution on an oscillating two-dimensional flat plate cascade in supersonic axial flow has been developed into a computer code. This unsteady aerodynamic code has shown good agreement with other published data. This code has also been incorporated into an existing aeroelastic code to analyze the NASA Lewis supersonic through-flow fan design.
Document ID
19880013871
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ramsey, John K. (Army Aviation Systems Command Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1988
Publication Information
Publication: NASA, Lewis Research Center, Lewis Structures Technology, 1988. Volume 1: Structural Dynamics
Subject Category
Structural Mechanics
Accession Number
88N23255
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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