RESEARCH ON PANEL FLUTTER OF CYLINDRICAL SHELLS.
Abstract
A theoretical study was made on the panel flutter characteristics of a ring and longeron stiffened circular cylindrical shell at high supersonic Mach numbers. This study is an extension of an earlier program and uses the cyclic reduction procedure developed there to simplify the flutter analysis. This actual reduction procedure has been included in this report for completeness. An improved modal analysis was employed in this study which leads to an increased understanding of the flutter behavior of such complex structures at the high supersonic Mach numbers. A method for extending the above analysis to the lower supersonic Mach numbers is also discussed. An investigation of the aerodynamic pressures on cylindrical shells in unsteady supersonic potential flow has also been carried out. A general solution for these aerodynamic pressures was obtained which is valid at both the high and low supersonic Mach numbers. The general solution was expressed in terms of Randall functions by reducing the unsteady flow problem to an equivalent steady flow problem through an appropriate transformation. Certain limiting cases of this general solution are presented along with their well-known flat plate counterparts. Finally, an analytical approximation is developed for the Randall functions which would be useful in a cylindrical shell panel flutter analysis. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1964
- Accession Number
- AD0430829
Entities
People
- Ronald O. Stearman
Organizations
- MRIGlobal