Vortex Behaviors of Rolled Supersonic Transport Configuration with Leading-Edge Flaps

Wind tunnel measurements were done to investigate the effect of leading-edge flaps on the rolling moment characteristics of the cranked arrow wing for the supersonic transport. Static rolling moment measurements, flow visualization studies, and crossflow velocity measurements by a particle image velocimetry were made at Re = 6.2 x 10... Static rolling moment measurements confirmed linear restoring moment at a ...16 deg for the models both with and without flap deflection. When the outboard leading-edge flap is deflected 12 deg, rolling moment hysteresis is observed at the roll angle of ...20 deg and ...20 deg. The experimental results indicate that the hysteresis is caused by different vortex breakdown behaviors on the inboard wing when the wing is rotated in the clockwise and counterclockwise directions.