Abstract
Numerical flutter simulation of a high-aspect-ratio transport type of wing in transonic region is presented. The aeroelastic responses of the wing are obtained by integrating compressible thin-layer Navier-Stokes (N-S) equations coupled with the equations of motion of the wing structure. The Yee-Harten implicit TVD scheme and the Wilson θ method are employed to integrate N-S equations and structural ones, respectively. The flutter boundaries are obtained at the angle of attack of 2 degrees and compared with experimental results. The flutter characteristics of this wing model are investigated and discussed. Furthermore, Limit cycle oscillations are found in the unstable region and the mechanism is clarified.
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