Low Reynolds number airfoil research is gaining importance because of its applicability to Micro Aerial Vehicles (MAVs), Unmanned Aerial Vehicles (UAVs), and vehicles designed for low-density planetary environments such as Mars. Laminar flow separation is a major problem associated with these Reynolds numbers which has lead to the study of a variety of separation control mechanisms. One such mechanism, an actuator designed to produce oscillatory airfoil camber, is the target of the presented research. Previously, experimental tests of such an actuator implemented in a NACA 4415 have been performed—this presentation focuses on the numerical simulations of this airfoil. A series of computations were performed for Reynolds numbers ranging from 25,000 to 100,000 and over a range of angles of attack and at multiple oscillation frequencies. Current comparisons with the available experimental data indicate that the numerical results capture the overall behavior of the low Reynolds number flow for actuating and non-actuating cases. Specifically, the addition of oscillating camber at a constant frequency significantly reduces the laminar separation relatively to the non-oscillating case at the same flow conditions. Collectively, these simulations expand on the results available from experiments, provide greater insight into the flow physics involved, and serve to guide further development of this promising flow control technique.