In recent years, the flow control method using plasma discharge, for example, a plasma actuator, has been attracting attention, because of its shorter response-time than conventional mechanical control devices such as flaps. In this study, a flat plate model with a small cavity under the surface was tested for the discharge experiment in the Mach 7 hypersonic wind tunnel in Kashiwa campus, the University of Tokyo. Two types of the discharge cavities were tested: a cavity with an orifice normal to the surface and a cavity with an orifice and a forward-facing-step inlet open to the boundary layer flow. A pair of tungsten rod-type electrodes were inserted into the cavity, and the applied voltage was 1kV at maximum using high-power capacitors. The discharge occurred intermittently and the time history of the discharge voltage was measured. The effect of the discharge on the flow field was visualized by the schlieren method. In the case of the intake moved slightly forward when the discharge occurred.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
模型表面内側に設けた放電室による極超音速境界層流れ制御の基礎実験
AA1830029007.pdf
(5.53MB)
