Accession Number : AD0604130

Title :   THERMAL STRESSES IN CONICAL SHELLS,

Corporate Author : RAND CORP SANTA MONICA CALIF

Personal Author(s) : Huth,J. H.

Report Date : 12 JUN 1952

Pagination or Media Count : 14

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)

Descriptors :   (*CONICAL BODIES, THERMAL STRESSES), (*AERODYNAMIC CHARACTERISTICS, CONICAL BODIES), PRESSURE, TEMPERATURE, LAMINAR BOUNDARY LAYER, GUIDED MISSILES, EQUATIONS, DIFFERENTIAL EQUATIONS, INTEGRALS, BESSEL FUNCTIONS

Distribution Statement : APPROVED FOR PUBLIC RELEASE