Accession Number:

AD0639711

Title:

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

Descriptive Note:

Corporate Author:

GRADUATE AERONAUTICAL LABS CALIF INST OF TECH PASADENA

Personal Author(s):

Report Date:

1966-07-01

Pagination or Media Count:

36.0

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 Donnells 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

Subject Categories:

  • Structural Engineering and Building Technology
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE