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
Descriptors:
Subject Categories:
- Structural Engineering and Building Technology
- Mechanics