Supersonic flutter analysis of infinite span plate, separated into array of rectangular panels, is presented; region between Mach 1 and 2 1/2 is of interest, and linearized three-dimensional aerodynamic theory is applied; elastic behavior of configuration is described by small deflection theory; partially clamped edge condition is obtained by introducing torsional restraint proportional to first derivative of transverse deflection along normal to edge; numerical results are given in terms of characteristic panel flutter parameters.
Flutter of flat plates with partially clamped edges in low supersonic region
AIAA J
AIAA Journal ; 3 , n 1
1965
6 pages
Aufsatz (Zeitschrift)
Englisch
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