Framework for T-tail flutter analysis

Abstract

The flutter analysis of T-tail aircraft poses challenges that are unique to this configuration, including the fact that the unsteady air loads are dependent on the steady load distribution and static deformation of the aircraft. In particular, the trim load on the horizontal stabilizer and the static deformation of the horizontal stabilizer, an induced dihedral effect, are significant. These effects are now well understood and accurate analyses can be made for a given set of conditions of incidence angle, elevator deflection and deformation. This paper considers the process required to perform the flutter analyses of a T-tailed aircraft.