The numerical simulations of transonic flutter of a T-tail are conducted using a 3D Navier-Stokes code which takes into account the in-plane motion of the horizontal tail plane (HTP). As the result of the simulation, the sharp transonic dip phenomenon of the flutter boundary, which is similar to that experienced in the transonic flutter experiment conducted at NASA for the T-tail of a wide-body transport airplane in 1975, is predicted. In the present simulation, the effect of angle of attack of the HTP on the flutter boundary and the characteristics of the flutter are also examined in detail. Most of the flutter and limit cycle oscillation (LCO) experienced around the bottom of the dip are the single-degree-of-freedom flutter where the first bending mode of the vertical tail plane is predominant.
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