Comparison of theory and experiment for nonlinear flutter of loaded plates

Published

Journal Article

The flutter behavior of clamped plates exposed to transverse pressure loadings, or buckled by uniform thermal expansion has been investigated theoretically, and the results compared with existing experimental data. Quasi-steady aerodynamic theory and von Karman's plate equations are employed. Two sets of in-plane boundary conditions are considered: 1) zero in-plane motion normal to the edges, and 2) zero in-plane stress at the edges. A modal expansion of the transverse deflection is used in conjunction with Galerkin's method to obtain a set of nonlinear ordinary differential equations which are integrated numerically to determine the flutter motion. Good correlation is obtained between experimental and theoretical flutter boundaries for plates exposed to a, static pressure differential. The stability boundaries of low aspect ratio plates with zero edge restraint are found to be more sensitive to pressure loads than are those of plates with complete edge restraint. Moreover, comparisons with available experimental data indicate that zero edge restraint is a good assumption for some panel configurations. Finally, it is indicated that fair agreement between theory and experiment can be obtained for buckled plates. © 1970, American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

Full Text

Duke Authors

Cited Authors

  • Ventres, CS; Dowell, EH

Published Date

  • January 1, 1970

Published In

Volume / Issue

  • 8 / 11

Start / End Page

  • 2022 - 2030

International Standard Serial Number (ISSN)

  • 0001-1452

Digital Object Identifier (DOI)

  • 10.2514/3.6041

Citation Source

  • Scopus