Virtual aeroelastic flight testing for the F-16 fighter with stores

Published

Conference Paper

In the following, we present computational aeroelastic flutter onset and limit cycle oscillation response trends for various stores and weapons configurations of the F-16 fighter. 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. However, slender body/wing theory is used as an approximate method in accounting for the unsteady aerodynamic effects of wingtip launchers and missiles.

Duke Authors

Cited Authors

  • Thomas, JP; Dowels, EH; Hall, KC; Denegri, CM

Published Date

  • November 5, 2007

Published In

  • Collection of Technical Papers U.S. Air Force T and E Days, 2007(Test and Evaluation

Start / End Page

  • 339 - 346

International Standard Book Number 10 (ISBN-10)

  • 1563478919

International Standard Book Number 13 (ISBN-13)

  • 9781563478918

Citation Source

  • Scopus