Flow control experiments were performed using nanosecond dielectric barrier discharge (NS-DBD) plasma actuators on a NACA 0015 airfoil with a flow approaching from the geometric trailing edge side, a condition anticipated to occur in slowed rotor compound rotorcraft. The Reynolds number based on the cord was fixed at 5.0·10~5 corresponding to a freestream flow of approximately 38 m/s, and an angle of attack of 15° was used. Plasma actuation was evaluated at both the aerodynamic leading and trailing edges of the airfoil. Excitation at the aerodynamic leading edge caused a significant decrease in the separation region and increase in the lift coefficient. Excitation over a broad range of frequencies at the aerodynamic trailing edge was found to significantly reduce organization of the large-scale wake structures. Combining both leading and trailing edge excitation was completely dominated by the aerodynamic leading edge excitation in almost all cases. Two exceptions were found where the resultant flow characteristics fell between those of the independent excitations.
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