Implicit large-eddy simulation (ILES) computations have been performed for canonical problems associated with flexible, flapping-wing micro air vehicles (MAVs). This computationally-intensive approach, which is able to directly model laminar/transitional/turbulent flow fields, requires the use of the best high performance computational platforms available. Results for the direct numerical simulation of the deep dynamic stall phenomenon over a rigid plunging airfoil section at transitional Reynolds numbers relevant to MAV systems are presented. Next, computations for two different flexible-wing geometries, a membrane-wing section and a three-dimensional, flexible-wing with an NACA0012 cross-section, are discussed. Finally, to investigate the relevant physics associated with a perching maneuver, computational results for a pitch, hold and return motion are examined. All computed results show good correlation with corresponding experimental measurements.
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