超音速流中におけるマイクロフラップによるデルタ翼ローリングモーメント制御

抄録

Numerical investigation of the rolling moment control of a delta wing using a micro-flap in supersonic flow is performed in the present study. So far, several experiments and CFD analyses regarding the micro-flap in subsonic flow have been reported, and the location of a leading edge separation vortex and its size are found to play a key role in producing the rolling moment. On the other hand, in supersonic flow, the mechanism of rolling moment generation is found to be different from that in subsonic flow. The leading edge separation vortex is not so much affected by micro-flap installation. However, a large pressure change behind the micro-flap is observed, which causes the rolling moment of the delta wing. Moreover, the rolling moment in the supersonic flow is generated only in one direction, unlike the subsonic flow, where it is produced in either direction.