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Supersonic unstalled flutterFlutter analyses were developed to predict the onset of supersonic unstalled flutter of a cascade of two-dimensional airfoils. The first of these analyzes the onset of supersonic flutter at low levels of aerodynamic loading (i.e., backpressure), while the second examines the occurrence of supersonic flutter at moderate levels of aerodynamic loading. Both of these analyses are based on the linearized unsteady inviscid equations of gas dynamics to model the flow field surrounding the cascade. These analyses are utilized in a parametric study to show the effects of cascade geometry, inlet Mach number, and backpressure on the onset of single and multi degree of freedom unstalled supersonic flutter. Several of the results are correlated against experimental qualitative observation to validate the models.
Document ID
19790002829
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Adamczyk, J. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Goldstein, M. E.
(NASA Lewis Research Center Cleveland, OH, United States)
Hartmann, M. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
E-9785
NASA-TM-79001
Meeting Information
Meeting: Meeting of the Propulsion and Energetics Panel
Location: Cleveland, OH
Country: United States
Start Date: October 23, 1978
End Date: October 27, 1978
Sponsors: AGARD
Accession Number
79N11000
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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