Uninhabited air vehicles are commonly designed with high-aspect-ratio wings, which can be susceptible to significant aeroelastic vibrations. These oscillations can result in a loss of control or structural failure, and new techniques are necessary to alleviate them. A multidisciplinary effort at Stanford developed a distributed flow control method that used small trailing-edge actuators, known as micro-trailing-edge effectors (MiTEs) to alter the aerodynamic loads at specific spanwise locations along an airplane wing. The actuators were based on a Gurney flap, which is a trailing-edge flap of small size and large deflection, allowing an increase in lift with a small drag penalty. The transient response caused by relatively rapid MiTE actuation was studied using particle image velocimetry in the near wake. The transient response was quasi-steady for dimensionless actuation times (t.Uinfinity/c) near unity. A shorter dimensionless actuation time of 0.2 produced a transient response with significant overshoot of the downwash velocity in the near wake. This indicated a nonmonotonic response of the aerodynamic loads for rapid actuation.


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    Title :

    Dynamic flow response due to motion of partial-span Gurney-type flaps


    Additional title:

    Dynamische Reaktion des Strömungsfeldes hinter einer Tragfläche infolge der Verstellung von Gurney-Klappen


    Contributors:

    Published in:

    AIAA Journal ; 42 , 9 ; 1729-1736


    Publication date :

    2004


    Size :

    8 Seiten, 11 Bilder, 2 Tabellen, 14 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English