THERMAL STRESSES IN CONICAL SHELLS,
Abstract
The paper considers the stresses in a conical shell of revolution resulting from aerodynamic pressure and thermal gradients. In particular the results are applicable to the conical tip of a missile flying at zero angle of attack; a numerical example is given for a temperature distribution typical of a laminar boundary layer. It is concluded that from the standpoint of eliminating high stresses, large temperature gradients both along a ray and across the shell thickness are most undesirable. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 12, 1952
- Accession Number
- AD0604130
Entities
People
- J. H. Huth
Organizations
- RAND Corporation