Supersonic Flutter of Simply Supported Isotropic Sandwich Panels.
Abstract
A theoretical solution using two-dimensional static aerodynamics is presented for the supersonic flutter characteristics of flat rectangular isotropic sandwich panels with simply supported edges. Tables and charts giving the values of the dynamic-pressure parameter required for flutter are presented for various values of panel length-width ratio, shear flexibility, and midplane stress. It is found that a decrease in transverse shear stiffness will usually lower the dynamic pressure required to induce flutter. However, for certain cases of midplane tension the opposite effect occurs. Panel mode shapes are also presented and a comparison is made of the two-mode Galerkin, the pre-flutter, and the exact flutter solutions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1966
- Accession Number
- ADA307268
Entities
People
- Larry L. Erickson
- Melvin S. Anderson
Organizations
- Langley Research Center