抄録
Flow separation is mostly an undesirable phenomenon and boundary layer control is an important technique for the separation problems on airfoils. The vortex generator jet method is an active control technique which provides a time-varying control action to optimize performance under a wide range of flow conditions because the strength of longitudinal vortices can be adjusted by varying the jet speed. In this study, wind tunnel tests for an airfoil installed active boundary layer control system using VGJs were performed. The experimental results indicate that the maximum lift coefficient increases 10%, and the stall angle is to rise by 2 deg in contrast to the case under no control. It was confirmed that our proposed system can suppress stall on the NACA0012 airfoil and the aerodynamic performance of the airfoil can be enhanced.
