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        Theoretical investigation of the flutter characteristics of supersonic cascades with subsonic leading-edge locus

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        Author
        Bell, James Keith
        Date
        1975-06
        Advisor
        Platzer, M. F.
        Second Reader
        Gawain, T. H.
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        Abstract
        Supersonic flow past a semi-infinite array of flat plate cascaded airfoils is analyzed using a linearized method of characteristics procedure. For a cascade having subsonic leading edge focus, but otherwise arbitrary geometry, frequency of blade oscillation, and interblade phase angle, pressure distributions and lift forces and moments are determined. These are used for flutter analysis and the determination of flutter boundaries. In addition, the linearized method of characteristics procedure is used to analyze supersonic flow through cylindrical shells. Pressure distribution and generalized forces are computed for arbitrary radius-to-length ratios, axial and circumferential mode numbers, and frequency of panel oscillation.
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        This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
        URI
        http://hdl.handle.net/10945/21087
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        • 1. Thesis and Dissertation Collection, all items

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          Weber, Stefan; Jones, Kevin D.; Ekaterinaris, John A.; Platzer, Max F. (Éditions scientifiques et médicales Elsevier SAS., 2001);
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          Transonic Flutter Computations for a 2D Supercritical Wing 

          Weber, S.; Jones, K.D.; Ekaterinaris, J.A.; Platzer, M.F. (1999);
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          Supersonic flow past two oscillating airfoils 

          Alexandris, Georgios (Monterey, California. Naval Postgraduate School, 1998-06);
          Supersonic flow past two oscillating airfoils is analyzed using an elementary analytical theory valid for low frequencies of oscillation. The airfoils may have arbitrary stagger angle. This approach generalizes Sauer' ...
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