Effects of camber and camber-change due to elastic deflection for aspect ratio 4.25 wings were examined for the classical unsteady problem of rectilinear translational acceleration. Direct force measurements and flow visualization by laser illumination of fluorescent dye allowed for the tracking of force history vs. evolution of the flowfield of rigid flat, rigid cambered, and flexible membranous wings. At low incidence (10 degrees and below), Wagner's approximation provides an accurate prediction of the timeevolution of lift for the rigid wings, beyond which flow separation leads to peaks in the force history and the camber-effect is no longer additive to the incidence effect. Both the rigid uncambered and cambered wings reach peak lift at 35 degrees, whereas the flexible wing experiences a form of stall-delay and reaches peak lift at 50 degrees. Due to the aeroelasticity of the flexible membrane, flow over the suction surface remains attached for much higher incidence angles than for the rigid wings. For incidence angles less than 30 degrees, the flexible wing's peak lift is lower than that of its rigid counterparts. However, beyond 30 degrees, the flexible wing experiences an aeroelastically-induced stall delay that allows lift to exceed the rigid analogs.
INTRODUCTIONThe impact of wing flexibility on aerodynamic performance has become a topic of interest among the micro air vehicle (MAV) community. Research on a wide range of natural fliers, from insects [1-3] to bats [4][5] aims to discover the aerodynamic benefit of membranous wings in the low Reynolds number flight regime. These natural fliers use thin, compliant wings as lifting surfaces, causing their wings to undergo large change in shape during flight [6]. Membrane wings have the potential to reduce the gross weight of micro air vehicles, while also introducing variable geometry (e.g. camber and twist) and improving stability to ensure robust flight characteristics over a wide range of harsh flight conditions.In the low Reynolds number regime typical of MAV flight (Re < 10 5 ), flow separation and vortex formation are common and provide sources of flow unsteadiness. It is important to characterize this unsteadiness in consideration of designing a controller to stabilize the vehicle from potentially damaging gusts or stall conditions. Comparisons of a two-dimensional flexible membrane along with its rigid cambered analog revealed a coupling between unsteady vortex shedding and dynamic structural response for the flexible wing, resulting in delayed stall and enhanced lift [7]. It is important to note that flapping wing MAVs depend heavily on transient, high lift mechanisms such as leading edge vortices (LEVs) in largely separated flow to generate lift.Studies focused on the effect of wing flexure in impulsively translating wings [8] concluded that wingtip flexure effectively diminishes the influence of the tip vortex (TiV) on the structure and trajectory of the LEV, allowing the LEV to remain connected and close to the wing. This is contrary to ...