Computational/experimental aeroelastic study for a horizontal-tail model with free play


Journal Article

A computational code has been developed for aeroelastic analysis for an all-movable horizontal tail, and a companion wind-tunnel test program has been conducted. The structural bending and torsional stiffness are based upon an experimental tail model that has served as the basis for free-play design criteria. A linear three-dimensional time-domain vortex-lattice aerodynamic model is used to study the flutter and also nonlinear limit-cycle oscillations induced by a free-play gap in the actuating mechanism at the root of the tail as well as the effects of the root rotation angle (nominal angle of attack) on limit-cycle-oscillation response and gravity loads. It is found that the root rotation angle, gravity loads, and the initial conditions all significantly affect the limit-cycle-oscillation behavior. The computed aeroelastic responses are compared with the experimental data. Copyright © 2012 by Deman Tang and Earl Dowell. Published by the American Institute of Aeronautics and Astronautics, Inc.

Full Text

Duke Authors

Cited Authors

  • Tang, D; Dowell, EH

Published Date

  • February 1, 2013

Published In

Volume / Issue

  • 51 / 2

Start / End Page

  • 341 - 352

International Standard Serial Number (ISSN)

  • 0001-1452

Digital Object Identifier (DOI)

  • 10.2514/1.J051781

Citation Source

  • Scopus