Abstract
This experimental study examines flow control authority of a quasi-DC (Q-DC) electric discharge in a cavity-based supersonic flow. Testing was performed with Mach 2 airflow using the Research Cell 19 facility at the U.S. Air Force Research Laboratory while varying pressure (), temperature (), gaseous fuel-injection rate [ standard L/min (SLPM)], and power of the electric discharge (). Schlieren imaging and pressure sensors were used to study changes to the flowfield and wall pressure distribution over the test section. The Q-DC electric discharge generates a shock wave that impinges on a rear-facing cavity and increases the pressure throughout the cavity up to 5%. A gas was injected upstream of the cavity to represent fuel injection in a scramjet engine. The flowfield changes due to the Q-DC discharge interaction with the fuel-related bow-shock wave, and shifts the shock train upstream. For injection rates of SLPM, the Q-DC discharge shifts the bow-shock reflection forward to impinge the cavity, thus showing a synergistic effect of the Q-DC discharge and the upstream injection. The maximum relative pressure increase during Q-DC operation with injection was . The control effectiveness parameter was defined and is approximately constant across the tested flow conditions.
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