EXPERIMENTS ON THE FLUTTER OF FLAT AND SLIGHTLY CURVED PANELS AT MACH NUMBER 2.81,
Abstract
Two series of panel flutter tests were carried out in the Jet Propulsion Laboratory's 12 inch supersonic wind tunnel. Flat and slightly curved panels were tested at Mach number 2.81. The flat, rectangular panels were designed to study two-dimensional flutter. They were clamped at front and rear with free sides which extended into the boundary layer at the sides of the tunnel. These panels flutter in a two-dimen sional mode which occurred at a thickness ratio approximately 15% different from the predictions of existing theory. One of the panels exhibited a three-dimensional ''rocking'' flutter which has not been observed or discussed before. A theory is developed for this type of flutter. The slightly curved panels were shallow circular cylindrical shells with the generators perpendic ular to the flow direction. These panels were all of aspect ratio one. It was found that the effect of curvature was destablizing and that the effect of internal pressurization was stabilizing. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1962
- Accession Number
- AD0419378
Entities
People
- William J. Anderson
Organizations
- California Institute of Technology