Accession Number : AD0639711

Title :   INFLUENCE OF AN AXIAL SUPERSONIC FLOW ON THE BUCKLING OF THIN CYLINDERS UNDER END COMPRESSION,

Corporate Author : GRADUATE AERONAUTICAL LABS CALIF INST OF TECH PASADENA

Personal Author(s) : Fung,Y. C.

Report Date : JUL 1966

Pagination or Media Count : 36

Abstract : The combined features of two classical problems of shell instability are discussed, namely, the buckling of a circular cylindrical shell under axial compression, and the panel flutter of such a shell in an axial supersonic flow. In this paper, the static buckling of a shell in a supersonic stream, mathematically described by Donnell's equations and by linear piston theory, is solved. A special assumption with regard to the aerodynamic drag force (or skin friction) is made to simplify the analysis. Closed form solutions are found and are applied to semi-infinite cylinders. Results are obtained for two types of simply-supported edges and two types of clamped edges. The influence of a supersonic flow on lowering the critical buckling load of a circular cylindrical shell under axial compression is shown. The remarkable difference between the aerodynamic effect of a leading edge and a trailing edge is demonstrated. In all the cases examined the leading edge is less stable than the trailing edge. (Author)

Descriptors :   (*SHELLS(STRUCTURAL FORMS), *BUCKLING), (*CYLINDRICAL BODIES, SUPERSONIC FLOW), LOADS(FORCES), FORCE(MECHANICS), STRUCTURAL PROPERTIES, PARTIAL DIFFERENTIAL EQUATIONS, BOUNDARY VALUE PROBLEMS

Subject Categories : Structural Engineering and Building Technology
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE