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Practical application of active flow control of high speed flows is dependent upon the development of simple and robust actuators that can produce high momentum and are reliable, low cost, and responsive and can be easily integrated. This paper presents an experimental investigation of the characterization and implementation of high bandwidth micro-actuators for the control of supersonic resonant flows. The striking feature of this micro-actuator is its high momentum mean flow along with high amplitude and a tunable frequency unsteady component. First generation micro-actuators are designed and their performance is tested in controlling the highly unsteady impinging jet flow field. The results show that the impinging tones are completely eliminated with the actuation of these micro-actuators, whereas, new peaks at a frequency different from the actuation frequency and its harmonics are observed in the spectra, the occurrence of which need to be further explored. A reduction of 3-4 dB in overall sound pressure levels (OASPL) is achieved over the range of test conditions.