細長飛翔体の大迎角飛行時における剥離流れの能動的制御に関する研究(流れの制御(2),一般講演)

概要

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When a slender body flies at high angle of attack, asymmetric separation vortexes are formed even behind an axis symmetric slender body, and the asymmetric vortexes act the side force on the body which leads to disturb the attitude control. We study on the active control of the separation flow behind the slender body. We address not only the linearly control of the side force but also the control of the pitching moment. The flow control experiment has been conducted in a wind tunnel using a cone-cylinder testing body and DBD plasma actuator as a flow control device. The side force coefficient can be linearly controlled within about +/-1.0 by flow controlling at the aft body (the cylinder part). The static stability angle can be controlled between 30 and 80 degrees by controlling the pitching moment when the center of gravity is at 55% position from the body tip.
2010-09-09