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

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.

Duke Scholars

Author Earl H. Dowell Thomas Lord Department of Mechanical Engineering and Materia ...