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Item Literature Review of the Aerodynamics of Flapping Flight in Micro Air Vehicle Applications(North Dakota State University, 2014) Morman, JoshuaBiological flapping wing flyers achieve flight maneuverability and efficiency in low speed flight environments that has not been replicated by man-made flyers. Micro Air Vehicle (MAV) design goals are to develop flyers that maintain flight in environments that biological flyers excel in which includes low speeds, hovering, and urban settings. This flight is characterized by flow phenomena that are not well understood such as: flow separation and vortical flow. The goal of this study is to perform a literature review about the aerodynamics of flapping flight and discuss the application to MAV design. The study will evaluate the design initiatives of MAV. Experimental and computational test methods are reviewed. Low Reynolds number aerodynamics are studied. The effects of airfoil aeroelasticity and geometry are discussed. Then, the application of the aerodynamics to flapping motions are reviewed. Finally, operational MAV designs are studied and recommendations are made to further advance the state of the art.Item Experimental Characterization of a Novel Integrated Flow Control Method(North Dakota State University, 2010) Baqui, Muhammad NiamulFlow control methods can be used in many areas of aerodynamics such as separation control, wind turbines, landing gears and micro satellites. Flow separation in the boundary layer is one of the fundamental problems of aerodynamics. Separated flow in the airfoil boundary layer causes the aircraft to stall. Blowing and Dielectric Barrier Discharge (DBD) Plasma Actuator based techniques have proven successful in limited applications of separation control. However, Blowing techniques require high pressure source and Plasma Actuators are only successful in low speed application. The current research incorporated experimental techniques in characterizing a novel integrated flow control method by combining blowing flow control with Dielectric Barrier Discharge (DBD) Plasma Actuator based flow control. Integrated control would be applicable in wider flow domain than individual plasma or blowing. Initially, characterization experiments were performed as a proof of concept for the integrated control and then, the integrated control was applied in airfoil separation control. Characterization experiments were performed with a vertically fired cylindrical jet having plasma actuator around the jet periphery. The cylindrical jet was used to simulate blowing. The results obtained from characterization experiments indicated 63% reduction in blowing ratio due to plasma addition. The integrated control was placed on NACA 0025 airfoil with blow opening at 25% x/C and plasma actuator at 25.5% x/C location. Windtunnel tests were performed at freestream velocities of 3 mis and 4.5 mis with airfoil angle set at 10 degree. Results indicate 110% increase in airfoil near wall velocity for 3mls when integrated control was applied. Separation was experienced in the region when other flow control methods were used.