73 巻 (2007) 727 号 p. 663-669
Effective location of plasma actuators for a flow separation control over a NACA 0012 airfoil is investigated by computational simulations. Single plasma actuator is located at 5%, 10% or 20% chord from the leading edge. The results indicate that the actuator located near the separation has a better capability to control flow separations. Separation is once avoided when a single actuator is located near the separation, another separation occurs from the trailing edge. This motivates to use multiple actuators and the separations are carried out for two actuators. The result shows the possibility that appropriate layouts of actuators can achieve high control performance with relatively low input voltage.