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

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; Jr, CMD

Published Date

  • 2007

Published In

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

Start / End Page

  • 339 - 346