A plunging-pitching aeroelastic apparatus has been developed to experimentally test new devices for flow and aeroelastic control. The purpose of the experiment is twofold: i) the first phase investigates the aeroelastic behavior of a two-dimensional wing section in post-flutter region, structurally and aerodynamically characterizing the aeroelastic model; ii) the subsequent experiment will be instrumental to test active flow control devices in both the pre- and post-flutter regimes. The design of the testing apparatus utilizes a linear and nonlinear cam spring system that allows testing at selected aeroelastic and flowfield conditions. The wing section is mounted to the aeroelastic test apparatus and tests have been conducted in the low speed Clarkson University Wind Tunnel Facility. Plunging and pitching accelerations of the wing during aeroelastic response have been recorded to study and compare the experimental results with the proposed mathematical models. Active flow control devices are bench tested and will be installed in a composite NACA 0018 airfoil at specified locations along the wing span. Zero Net Mass Flux (ZNMF) devices, such as synthetic jets actuators (SJA) and frequency driven voice coils, are under investigation to demonstrate their ability to actively change the flowfield for improved aeroelastic wing performances. Numerical simulations have already demonstrated improved performance regarding flow and aeroelastic characteristics due to active flow control. Experimental investigation, numerical studies, and corresponding analytical models are provided and pertinent conclusions are discussed.
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