Wing-fuselage flutter of large aeroplanes

Abstract

A general theoretical method is described which takes into account a large number of degrees of freedom and is based on the design data for the aeroplane. The problem specifically investigated is the symmetrical flutter of a particular aircraft. Twelve degrees of freedom are assumed to cover pitching and translational motion of the whole aeroplane, flexure and torsion of the wings, and fuselage vertical bending. The tailplane is regarded as rigid. In the case considered, estimates indicate that the lowest critical speed is well above tile maximum design speed of the aeroplane. The influence of the additional degrees of freedom associated with movements of the control surfaces is not considered.