抄録
We carried out both aerodynamic forces measurements and flow visualization tests of a NACA0012 airfoil model at Re = 30,000 in order to verify what kind of effect does operating of a pulsed plasma actuator on both flow field and aerodynamics of the airfoil. Modulation frequency of pulsed operating mode of the plasma actuator was varied as non-dimensional modulation frequency F^+ from 1 to 10. The aerodynamics of the airfoil were improved by operating of the plasma actuator regardless of operating mode. And stall characteristics were clearly changed by pulsed operating mode that both the maximum lift value and the stall angle of attack were increased by depending on F^+. The flow field over the airfoil in pulsed operating mode show different characteristics from continuous operating mode; vortices were shed simultaneous with modulation frequency f_m and vortex structure including vortex street formed reattached turbulent flow on the airfoil. This change of flow phenomenon by depending on F^+ contributes suppression of extensively separation on the airfoil, therefore, it is important to clarify the details of relationship between the change of F^+ and the flow field which influenced by operating of pulsed plasma actuator.
