Plasma actuator is one of the newest devices in flow control techniques which can delay separation by inducing external momentum to the boundary layer of the flow. The purpose of this paper is to simulate a NLF0414 airfoil both experimentally and numerically in presence of the body force vector induced by a specific plasma actuator. For this reason, the simulation is done both numerically and experimentally for a NLF0414 airfoil with the compressible 25 m/s velocity airflow in two different cases: with no plasma actuator located on the airfoil and with body force produced by a plasma actuator located on the top of the airfoil in order to investigate the effect of plasma on the flow passing over it. The results showed that presence of a plasma actuator on the top surface of the airfoil, close to the separation point, transferred the separation point from x=16 mm to x=41 mm at the angle of attack of 18 degrees. This separation delay caused a 35% increase in the ratio of lift to drag coefficient or the efficiency of the airfoil in the same angle of attack.

Keywords: Plasma Actuator, Active Flow Control Method, Separation Point, Stall Angel

Full-Text [PDF 1275 kb]   (5265 Downloads)