Theoretical and experimental panel flutter studies in the Mach number range 1.0 to 5.0
This paper describes the methods and results of a careful, coordinated experimental and theoretical investigation of the flutter of flat, rectangular, isotropic panels at supersonic Mach numbers. A broad spectrum of Mach numbers (1.1-5.0) and length-to-width ratios (0.46-4.11) is covered. In Part I, the theoretical calculations are based upon classical, small, deflection-plate theory and three-dimensional, unsteady, aerodynamic theory, as well as simpler theories. In addition, the effect of the dynamics of the air in a sealed cavity beneath the panel is accounted for in the theory. In Part II, the experimental program is described, including presentation of pertinent data and comparison with theory. © 1965 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
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