FREQUENCY EFFECTS IN PANEL FLUTTER OF CYLINDRICAL SHELLS,
Abstract
The expression for the pressure coefficient on a vibrating cylindrical shell of finite length in unsteady supersonic flow is simplified. The expression is valid at high values of Mach number and is based on the quasisteady approximation when only first order terms in vibration frequency are considered. The kernel functions arising in the expression for the pressure coefficient are tabulated and shown graphically for a series of circumferential modes. It is anticipated that the revised expression will be simpler to use than the earlier expression when introduced into the full panel flutter equations. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1964
- Accession Number
- AD0603961
Entities
People
- M. Holt
- R. A. Brown
Organizations
- University of California, Berkeley