부산대학교 도서관

A plasma actuator is a simple device that can control flow with low power supply, so this is very practical and several applications have been proposed by many researchers. In this paper, a numerical method for simulating the flow with a plasma actuator is proposed, and it is applied to supersonic flow as well as subsonic flow. This method adopts unstructured mesh so that it can be employed for complex geometries. A numerical model proposed by Suzen et al. is used for simulating the phenomena caused by a plasma actuator, and TAS-code is employed for the flow field prediction. First, this paper validated the proposed method through two test calculations for subsonic flow; the Hump model used at CFD validity workshop in NASA Langley and then the NACA0015 airfoil. According to the results of the subsonic test calculations, the present method was able to predict the effects of the plasma actuator to the flow separation correctly. Finally, a calculation with the ramp model is conducted to control the shock wave, and its capability to control the shock wave through the shift in the shock wave location was confirmed.