Aiaa 2001–0293 Active Control of Separation on a Wing with Conformal Camber
نویسندگان
چکیده
A preliminary investigation of a wing with a conformal camber is discussed. The wing uses an adaptive actuator mounted internally to alter the shape of the suction surface which results in a change in the effective camber by increasing the maximum thickness and moving the location of maximum thickness aft. Since the actuator motion can be altered continuously, this allows the wing shape to be either static or dynamic. For the static mode, effects of profile perturbations are tested in a wind tunnel and tow tank to determine the change in wing efficiency due to variations in the camber at low Reynolds number. Various actuator locations and frequencies are tested from Re = 2.5 · 10 4 to Re = 2 · 10 5 at varying angles of attack. Preliminary comparisons are made with numerical predictions to demonstrate the effect of adaptive wing shaping on flight performance and the difficulty of predicting separated flow at low Re. For the dynamic mode, a wing with 5 modular span-wise sections each with a separately controlled internal actuator was constructed. The dynamic effects are currently being examined.
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