Theoretical investigation of the flutter characteristics of supersonic cascades with subsonic leading-edge locus
theoreticalinves00bell.pdf (10.58Mb)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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