Unsteady transonic, vortex-dominated flow around a 65°-sharp edged, cropped-delta undergoing pitching and rolling oscillations has been investigated computationally. The wing mean angle of attack is 20° and the freestream Mach number and Reynolds number are 0.85 and 3.23 x10~6, respectively. The initial conditions of the flow at 20° angle of attack are characterized with a terminating transverse shock and vortex-breakdown of the leading-edge vortex cores. A fine O-H grid of 125x85x84 points in the wrap-around, normal and axial directions; respectively is used in the computational applications. The solutions are obtained using the unsteady, compressible, full Navier-Stokes equations which are integrated using an implicit, upwind, flux-difference splitting, finite-volume scheme. The computational applications cover two cases. In the first case, the wing is forced to oscillate in pitch around an axis at the quarter-chord length with an amplitude of 4° and a reduced frequency of π. In the second case, the wing is forced to oscillate in roll around the axis of geometric symmetry with an amplitude of 5° and a reduced frequency of 2π.
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