Abstract
Flutter calculations were carried out on the results of fundamental wind-tunnel experiments on tip-fin configuration wings. In the experiments, mild flutter has been observed within a certain range of flow speed which was well below the violent flutter point. This mild flutter seems to be peculiar to the tip-fin configuration because its flutter mode couples with the wing torsion and the motion of the rudder on the tip-fin. Since the wing has the non-coplanar configuration with a partial control surface, the non-planar doublet-point method was utilized to calculate the subsonic unsteady aerodynamic forces of the control surface deflection as well as of the wing deformation. The results of the analysis show excellent agreement with those of the wind-tunnel experiments. It clearly explains the mild flutter due to the rudder motion on a tip-fin.
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