Theoretical predictions of F-16 fighter limit cycle oscillations for flight flutter testing

A computational investigation of the flutter onset and limit cycle oscillation behavior of various F-16 fighter weapons and stores configurations is presented. A nonlinear harmonic balance compressible Reynolds-averaged Navier-Stokes computational fluid dynamic flow solver is used to model the unsteady aerodynamics of the F-16 wing. Slender body/wing theory is used as an approximate method for accounting for the unsteady aerodynamic effects of wing-tip launchers and missiles. Details of the computational model are presented along with an examination of the sensitivity of computed aeroelastic behavior to characteristics and parameters of the structural and fluid dynamic model. Comparisons with flight-test data are also shown. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

Full Text

Duke Authors

Cited Authors

  • Dowell, EH; Thomas, JP; Hall, KC; Jr, CMD

Published Date

  • 2009

Published In

Volume / Issue

  • 46 / 5

Start / End Page

  • 1667 - 1672

International Standard Serial Number (ISSN)

  • 0021-8669

Digital Object Identifier (DOI)

  • 10.2514/1.42352

Citation Source

  • SciVal