PANEL FLUTTER ANALYSES AND EXPERIMENTS IN THE MACH NUMBER RANGE OF 5.0 TO 10.0
Abstract
Panel flutter experiments and analyses were conducted from 5.0 to 10.0 for two basic panel configurations. One configuration consisted of flat, rectangular, isotropic panels clamped on all four edges; the other configuration consisted of flat, rectangular, structurally two-dimensional panels clamped on leading and trailing edges with free side edges. Extensive vibration tests have been conducted and are reported. Flutter tests of the clamped-clamped panels were conducted to evaluate the effects of length to width ratio, thickness, static pressure differential, and Mach number (M = 5 to 6). Flutter tests of the clamped-free panels were conducted to determine the effects of midplane stress and Mach number (M - 5 to 10). (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1964
- Accession Number
- AD0351273
Entities
People
- D. J. Ketter
- H. M. Voss
Organizations
- Boeing