Accession Number : AD0642129

Title :   A THEORETICAL INVESTIGATION ON THE AEROELASTIC STABILITY OF ISOTROPIC CYLINDRICAL SHELLS AT BOTH THE HIGH AND LOW SUPERSONIC MACH NUMBERS.

Descriptive Note : Final technical rept.,

Corporate Author : MIDWEST RESEARCH INST KANSAS CITY MO

Personal Author(s) : Carter,Larry ; Stearman,Ronald

Report Date : OCT 1966

Pagination or Media Count : 78

Abstract : The study includes an investigation on the aeroelastic stability of thin isotropic cylindrical shells over the Mach number range 1.2 to 3. The analysis coupled the Donnell shell equations with a linear piston theory to approximate the aerodynamic forces at the high supersonic Mach numbers while a slender body theory was used to approximate the aerodynamic forces at the low supersonic Mach numbers. The influence of the shell's structural boundary conditions and initial stresses on its aeroelastic stability was also investigated. This included a study of the shell stability around both its deformed and undeformed state, the deformed state being due to the initial stresses in the shell. The theoretical results were finally compared with recent experimental studies conducted at both the high and low supersonic Mach numbers. (Author)

Descriptors :   (*SHELLS(STRUCTURAL FORMS), AEROELASTICITY), (*CYLINDRICAL BODIES, AEROELASTICITY), STABILITY, SUPERSONIC FLOW, DEFORMATION, STRESSES, AERODYNAMIC LOADING, THEORY

Subject Categories : Fluid Mechanics
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE