Abstract: Experiments were performed in NASAs SW-2 cascade facility to compare three trailing edge actuation concepts to a 3D airfoil section with no trailing edge treatment. At a Reynolds number of 105, trailing edge pulsed ejection using fluidic oscillator devices was shown to fill the momentum deficit in the wake more uniformly than other actuators tested, with expected benefits for tonal noise in engine fans. Furthermore, pulsed ejection was found to alter the acoustic signature of the wake to redu…