Abstract
The aeroelastic behavior associated with control surfaces is of particular practical interest The treatment of the control surface in a computational fluid dynamics based simulation is complicated by the change in topology of the geometry as the flap edge is exposed. This paper evaluates the use of a treatment which blends the flap edge into the wing. This simplifies the mesh treatment by avoiding topological changes. The influence of the treatment of the forced flap motions on the aerodynamic responses of the rigid benchmark active control technology wing and a flexible supersonic transport wing is evaluated. Comparison is made with results obtained when the flap edge is exposed. It is shown that the predictions from the blended treatment give similar results, including local effects on the control surface, to calculations which include the flap edge effects.
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