Recently two flutter analyses have been developed at NASA Lewis Research Center 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. The details of the development of the solution to each of these models have been published. The objective of the present paper is to utilize these analyses 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 from this study are correlated against experimental qualitative observation to validate the models.


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    Title :

    Supersonic unstalled flutter


    Contributors:

    Conference:

    NATO, AGARD, Meeting of the Propulsion and Energetics Panel ; 1978 ; Cleveland, OH


    Publication date :

    1978-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Supersonic unstalled flutter

    Adamczyk, J. J. / Goldstein, M. E. / Hartmann, M. J. | NTRS | 1978


    Supersonic Unstalled Flutter

    J. J. Adamczyk / M. E. Goldstein / M. J. Hartmann | NTIS | 1978


    Experimental Modeling of Unstalled Supersonic Turbofan Flutter

    Ronald E. Riffel / Sanford Fleeter | AIAA | 1981