1931 Flow Reattachment over an Airfoil using Surface Plasma Actuator
Details
An experimental investigation of flow separation control over an airfoil has been carried out using yawed RF glow-discharge surface plasma actuators. Flow visualization using smoke injection and smoke wire techniques, as well as PIV measurements, have been conducted in a wind tunnel to demonstrate the ability of surface plasma in reattaching a separated flow. A short surface plasma electrode with different yaw angles was placed over a NACA 0024 airfoil at x/c=0.3 at 7° of angle of attack, where the flow normally separates without control The Authors were able to show the suppression of global flow separation by surface plasma-induced flow. The mechanism of flow reattachment by surface plasma is quite different from other type of actuators in that large-scale streamwise vortices seem to playa key roll
