The multidisciplinary problem of tail buffeting is
solved using three sets of equations. The first set
is the unsteady, compressible, full Navier-Stokes
equations which are used for obtaining the flowfield
vector and the aerodynamic loads. The second set is
the coupled aeroelastic equations which are used for
obtaining the bending and torsional deflections of
the tail. The third set is the grid-displacement
equations which are used for updating the grid
coordinates due to the tail deflections. For the
computational applications, a sharp-edged delta wing
of aspect ratio one and a rectangular vertical tail
of aspect ratio one placed in the plane of geometric
symmetry behind the wing are considered. The
configuration is pitched at a critical angle of
attack (α = 38°) which produces asymmetric,
vortex-breakdown flow from the delta wing primary
vortices. The results show the effects of coupled
and uncoupled bending-torsional responses and the
effects of Reynolds number.