Abstract
In order to see whether the divergence phenomenon of a transport-type high-aspect-ratio forward-swept wing can be effectively eliminated by aeroelastic tailoring, experimental studies have been performed focusing attention especially on the transonic regime. The transonic flutter/divergence boundaries of the two wind tunnel models, one of which simulates the tailored full-scale wing and the other of which simulates the non-tailored one, have been determined. The tailored model has experienced flutter as predicted by the linear theory which employs the Doublet Lattice Method; i.e., the divergence phenomenon is suppressed by aeroelastic tailoring. The non-tailored model has experienced flutter, contrary to theoretical prediction, which is conjectured as “Shock Stall Flutter”, in which the shock-induced flow separation plays the dominant role. By comparing the nondimensional flutter boundaries of the two models, it is shown that, by aeroelastic tailoring, the transonic flutter characteristics of this particular wing can be improved about 60–80% over that of the non-tailored wing.
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