It has been shown that Surface Dielectric Barrier Discharge (SDBD) Plasma Actuator (PA) can be used for flow separation control at subsonic speeds. It has also been shown that it is possible to control supersonic shock geometry using SDBD PA to a certain extent. The current work is aimed at examining shock effects on the operation of a SDBD PA. Simulations are performed under standard temperature and pressure conditions for a plasma generated by a 1.2 kV SDBD PA for a period of approximately 100 ns and compared to similar simulations with the addition of a normal shock. It is found that a normal shock corresponding to an upstream Mach number of 2 is sufficient to reduce the ion density by a factor of 10 and approximately stop the plasma front from further downstream propagation or ionization.
AIAA Aerospace Sciences Meeting, 2018
Department of Mechanical and Aerospace Engineering

Murzionak, A. (Aliaksandr), Etele, J, & Pimentel, R. (Rogerio). (2018). Study of surface dielectric barrier discharge plasma actuator in supersonic flow. In AIAA Aerospace Sciences Meeting, 2018. doi:10.2514/6.2018-1294