This work is part of a larger study that includes the development of high-frequency MiTE (miniature trailing-edge effector) actuators, computational and experimental measurements of the steady-state and transient response of an airfoil to flap actuation, and the implementation of a control system on a simple flexible wing. This Note discusses the measured load response of a wing at moderate Reynolds number as a result of a set of 16 MiTEs. Full-span tests indicate that the airfoil lift and pitching moment at a given angle of attack can be considerably altered, which implies that MiTEs are capable of the significant loads changes necessary for control. The small gaps between MiTEs (5% of the actuator span) cause no notable performance degradation. Partial-span tests about midspan show a linear response with changes in flap span, a result that should simplify control design. The load responses can also be superposed, even if the actuators are not adjacent to each other. Finally, single flaps exhibit a spanwise influence at least 10 flap spans away, demonstrating a considerable nonlocal effect. This could be an issue with designing a control system, as the MiTE concept was devised in the hopes that each flap could influence the loads at a particular section. Although the strongest effects are directly at the flap, they are clearly not limited to a small spanwise region. Overall, these experiments have shown that MiTEs are good candidates for the development of a system for damping active aeroelastic instabilities.
Experimental aerodynamics of mesoscale trailing-edge actuators
Experimentelle Untersuchung des aerodynamischen Einflusses von Stellklappen an der Hinterkante von Tragflächen
AIAA Journal ; 40 , 12 ; 2538-2540
2002
3 Seiten, 4 Bilder, 7 Quellen
Aufsatz (Zeitschrift)
Englisch
Adaptive Trailing Edge: Specifications, Aerodynamics, and Exploitation
Springer Verlag | 2015
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