Aerodynamic boundary layer effects on flutter and damping of plates
A previously developed shear flow model for describing the aerodynamic pressures on a moving flexible wall in a boundary layer type flow is utilized to perform stability (flutter) and response analyses for elastic plates. Results for flutter boundaries and damping in the subflutter range are presented and compared to available experimental data. Agreement between theory and experiment is generally good except for damping at low supersonic Mach numbers. © 1973, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
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