Miniature trailing edge effectors (MiTEs) are small flaps (typically 1% to 5% chord) actuated with deflection angles up to 90 degrees. The small size, combined with little required power and good control authority enables the device to be used for high bandwidth control. Numerous experiments and computational simulations have been conducted for two dimensional airfoils with miniature flaps. However the three-dimensional effects of these devices haven’t been extensively investigated. The present study examines the steady three dimensional aerodynamics of MiTEs using incompressible Navier-Stokes flow solver. Preliminary contents • Spanwise lift distribution Preliminary computation shows that the influence of a single MiTE is widely distributed along the entire span of a wing. Spanwise lift distribution will be investigated. • Spanwise length of a individual actuator Since MiTEs do not usually encompass full span, it is necessary to investigate the effect of the spanwise length, in addition to the height. The influence of the length of MiTE on the control effectiveness will be examined. • Gap If more than two MiTEs are actuated separately, Gaps are required between the MiTEs, especially when the wing is flexible. Changes in the control effectiveness and drag due to the gaps between the actuators will be investigated. Doctoral Candidate, Department of Aeronautics and Astronautics, AIAA Student Member Professor, Department of Aeronautics and Astronautics, AIAA Fellow 1 2nd AIAA Flow Control Conference 28 June 1 July 2004, Portland, Oregon AIAA 2004-2693 Copyright © 2004 by Hak-Tae Lee. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
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