Fluid-structure interaction analysis is carried out to find the transonic flutter boundary for a realistic high aspect-ratio main wing of a typical medium-sized civil transport aircraft having supercritical wing section and twist distribution. We consider two cases in which the interaction analysis starts either from the static aeroelastic equilibrium shape or from the jig shape. It is found that both cases could determine the transonic dip of the flutter boundary equally well. However, the case of starting from the jig shape is shown to determine the flutter boundary substantially faster than the case of starting from aeroelastic equilibrium shape.
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