For the near-stall and fully stalled regime, where separation control is of interest, a limited amount of wing movement is always present. This is especially the case for high aspect ratio wings that exhibit some degree of structural flexibility such as seen on the X-56A. For the airfoil of the X-56A, wing section simulations were carried out for chord-based Reynolds numbers of Re=100,000 and 200,000. Below static stall (α≤12deg) a laminar separation bubble forms that gradually moves upstream towards the leading edge as the angle of attack is increased. When the wing section is subjected to high frequency plunging motions (2<k<4) coherent structures form above the suction surface. A low-frequency plunging motion (k=0.7) on the other hand results in a periodic growing and shrinking of the suction side trailing edge separation and an intermittent shedding of coherent structures. The simulation data for the latter are in reasonable agreement with University of Arizona wind tunnel data. Static wing section simulations for α=15deg revealed a periodic bursting of a laminar leading edge bubble with a dimensionless frequency of f≈0.07 and large lift and drag coefficient fluctuations. Based on a Proper Orthogonal Decomposition of the unsteady flow data three-dimensional modes with spanwise wavelengths of 80% and more of the chord length were identified.