FLOW CONTROL AROUND A NACA 0015 AIRFOIL WITH DBD PLASMA ACTUATOR PLACED AT CHORD DIRECTION AS VORTEX GENERATOR
Rafet GUNAYDIN, Yahya Erkan AKANSU, Hurrem AKBIYIK and Mehmet SEYHAN
An experimental study is carried out to investigate the influence of dielectric barrier discharge (DBD) plasma actuator on flow around a NACA 0015 airfoil at Re = 5x104. DBD plasma actuator starting at x/C = 0.1 is mounted to NACA 0015 airfoil at chord direction to increase lift coefficient (CL) and postpone stall. Measurements are performed at the actuator angle of = 0, 30, 60 and 90. Lift force measurement is implemented by using the load cell between = 0 and 15. The results indicated that stall angle is postponed from 9 to 11 and CL is significantly improved at post-stall region.