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As is well known, the flutter speed of T-tail depends strongly on the steady lift or dihedral angle of the horizontal tail plane. The unsteady rolling moment acting on the horizontal tail plane oscillating in yaw and sideslip plays the critical roll for this phenomenon. In this paper, a numerical method based on the 3D NavierStokes equations for computing the subsonic and transonic flow for a wing oscillating in yaw and sideslip is presented. By introducing a new coordinate system oscillating in yaw and sideslip, the existing 3D Navier-Stokes code is easily modified to account for the in-plane motions. The calculated rolling moments show a good agreement with the existing experimental data obtained for incompressible flow, and the effect of compressibility, especially the effects of the shock wave in transonic flow on the rolling moment are clarified.

Subsonic and Transonic Flow Simulation for a Wing Oscillating in Yaw and Sideslip