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 ( P 0 = 2.3 4.5    bar ), temperature ( T 0 = 290 590    K ), gaseous fuel-injection rate [ m ˙ = 0 3000 standard L/min (SLPM)], and power of the electric discharge ( W pl = 14 22    kW ). 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 m ˙ = 1500 3000 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 11 % . The control effectiveness parameter η was defined and is approximately constant across the tested flow conditions.


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    Title :

    Flow Control in Supersonic-Cavity-Based Airflow by Quasi-Direct-Current Electric Discharge


    Contributors:

    Published in:

    AIAA Journal ; 57 , 7 ; 2881-2891


    Publication date :

    2019-03-21


    Size :

    11 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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