2017 Volume 9 Issue 1 Pages 1-8
The advantage of a trielectrode (TED) plasma actuator in the flow separation control on the two two-dimensional airfoil model has been investigated experimentally in 30 m/s uniform flow ( Re = 6.0×105). Two exposed electrodes are set on the surface o f a NACA0012 airfoil model. For driving SDBD and TED plasma actuators separately, one exposed electrode for applyin g AC voltages is located at the leadingleading-edge, and DC voltages is applied to another one pla ced in 41.43 mm downstream from the leading edge. The flow field around the model was analyzed using time time-resolved PIV in a wind tunnel . The results indicated superior performance of the TED plasma actuator in separation delay when a high negative voltage ( Vdc = -20 kV) was applied, compared to the SDBD p lasma actuator. At the same time, the TED plasma actuator showed higher efficiency in energy consumption, when compared in terms of thrust generated per power supplied.
