The effect of steady tailplane lift on the subcritical response of a subsonic T-tail flutter model

Abstract

An aeroelastic model of an aircraft T-tail has been tested in a low speed wind tunnel. The purpose of the programme was firstly to check the validity of a method for calculating the aerodynamic forces acting on a T-tail oscillating about zero mean incidence. The secondary purpose was to measure the effect of tailplane incidence on aeroelastic behaviour, and to develop a method of calculation to take account of steady lift on the tailplane in the evaluation of flutter and sub-critical response. The Report presents the results of the tests and of the calculations, and shows that theory and experiment are in broad agreement, although accurate experimental data become difficult to obtain under certain conditions.