A Theoretical and Experimental 5tudy of Supersonic Panel Flutter of Circular Cylindrical Shells with Clamped Ends

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Abstract
The supersonic panel flutter of circular cylindrical shells with clamped ends is studied analytically and experimentally for the case of no inplane stress as a fundamental study. Using the two-mode approach and GALERKIN'S method, the panel flutter boundary, frequency and circumferential mode are obtained in the linear theory. The longitudinally seamed cylinders with 110mm diameter, 110mm length and 0.05-0.08mm thickness were made of super-invar in order to avoid the effect of temperature variation. The static pressure differential between two surfaces of the shell was automatically controlled so as to be zero in order to avoid its effect. The cylinder was tested at Mach number 2. The dynamic pressure was gradually increased and the occurence of the panel flutter was clearly observed in the oscillograph of the deflection and the records of the high speed camera. A good agreement between the analysis and the experiment is obtained for the flutter boundary, but not obtained for the flutter mode and frequency.

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