A THEORETICAL INVESTIGATION ON THE AEROELASTIC STABILITY OF ISOTROPIC CYLINDRICAL SHELLS AT BOTH THE HIGH AND LOW SUPERSONIC MACH NUMBERS.
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MIDWEST RESEARCH INST KANSAS CITY MO
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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 shells 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
- Fluid Mechanics