The objective of this thesis was to study flow characteristics and aerodynamic parameters of an optimized low Reynolds number airfoil with a rotating cylinder at its trailing edge for application in Micro Aerial Vehicles (MAVs). The airfoil had a chord length, a width, and a thickness of 15.24 cm, 30.48 cm, and 1.6 mm, respectively. Investigations of flow characteristics and aerodynamic parameters were performed using the CFD software, STAR-CCM+, by CD-Adapco. The freestream mean velocity was 10 m/sec. which corresponds to a chord length Reynolds number of 104,400. The simulations were performed at five different Angles of Attack (AOA), 0, 5, 10, 15 and 30 degrees, with and without cylinder rotation. Results indicate 53% improvement in lift to drag ratio of the airfoil at a velocity ratio of 1.66 with rotation, as compared to corresponding condition without cylinder’s rotation. Further analyses were conducted with velocity ratios of 1 and 0.53 and the results indicate increased lift to drag ratio in both conditions but not as significant when the velocity ratiofs was at 1.66.