ボルテックスジェネレータ型PAとスパン型PAを駆使した翼周り流れの剥離制御

抄録

Large-eddy simulations on a separation control flow around NACA4418 airfoil have been conducted. In the separation control, a vortex-generator type plasma actuator (VG-PA), spanwise type plasma actuator (SP-PA) and combination of these actuators (VG-to-SP) have been adapted. The configuration of the plasma actuator for the VG-PA case is set based on the previous experimental research. SP-PA is set at 0.05 times of the chord length from the leading edge. The Reynolds number is 35,000 and the angle of attack is 18 deg. The lift coefficient of the VG-PA case becomes most improved. The VG-to-SP case shows a larger lift than that of the SP-PA case. From the flow development of the VG-to-SP case, the VG-PA plays a role to suppress the massive flow separation in the initial stage of the flow control. Then, the SP-PA plays a role to keep the attached flow after the quasi-steady control flow by the VG-PA. Since the advantage of each plasma actuator type can be used, the control strategy in this study becomes effective control.