24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-4.1.3

NON-LINEAR VORTEX BEHAVIORS OF ROLLED SUPERSONIC TRANSPORT CONFIGURATION WITH LEADING-EDGE VORTEX FLAPS

K. Rinoie, M. Shirotake, D. Y. Kwak*
Department of Aeronautics and Astronautics, University of Tokyo, Tokyo, 113-8656,, Japan; * Japan Aerospace Exploration Agency, Tokyo, 181-0015, Japan

Keywords: edge flap, rolling moment, vortex interaction, SST

Wind tunnel measurements were done to investigate effects of vortex flaps and leading-edge flaps on the rolling moment characteristics of cranked arrow SST wing. PIV measurements indicated the rolling moment hystereses are caused by the movement of vortex breakdown position on the inner wing, when outboard leading-edge flaps are deflected.

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