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- W2009258081 abstract "A supersonic flutter analysis of an infinite span plate, which is separated into an array of rectangular panels, is presented. The region between Mach 1 and 2/ is of specific interest, and linearized three-dimensional aerodynamic theory is applied. The elastic behavior of the configuration is described by small deflection theory. The partially clamped edge condition is obtained by introducing a torsional restraint proportional to the first derivative of the transverse deflection along the normal to the edge. Numerical results are given in terms of characteristic panel flutter parameters. The effects of Mach number, aspect ratio, number of panels in the chordwise direction, panel material, and altitude are examined." @default.
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- W2009258081 date "1965-01-01" @default.
- W2009258081 modified "2023-09-27" @default.
- W2009258081 title "Flutter of flat plates with partially clamped edges in the low supersonic region" @default.
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- W2009258081 doi "https://doi.org/10.2514/3.2781" @default.
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