Forebody vortex control

Abstract Because conventional fighter aircraft control surfaces (e.g. rudder) become ineffective at high angles of attack, alternate means of providing aerodynamic control are being explored. A prime potential source for improved control power is the vortex flowfield existing on typical fighter aircraft forebodies. Several techniques to manipulate the forebody vortices to produce controlled forces and moments at high angles of attack have been investigated by a number of researchers in the past few years. This paper reviews some of the reported research results and discusses the merits of several methods applied directly to the forebody, including: (1) movable strakes, (2) blowing surface jets, (3) blowing and suction through surface slots, (4) suction through surface holes, and (5) miniaturized rotatable tip strakes. All of these were found to be effective over a varying range of angles of attack and sideslip. Most of the methods work on the basis of boundary layer separation control. The presence of closely spaced forebody vortices enhances the effectiveness since controlling the separation controls the vortices which, in turn, creates large changes in the forebody forces. Regardless of which method is employed, the maximum effectiveness is realized if it is applied near the forebody tip. The advantage of one method over another will depend on the configuration and specific performance requirements.

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