An experimental study of the development of a pulsed volume discharge with pre-ionization in a non-uniform supersonic air flow near the wedge in the shock tube channel and the gas-dynamic flow arising after the discharge has been carried out. Plasma configurations arising near the bottom of the wedge were studied when discharge initiating at various stages of unsteady flow. The conditions for the self-localization of a volume discharge into the vortex zone behind the wedge are analyzed at the Mach number of shock wave 2.6-3.5 (flow Mach number up to 1.50, density up to 0.15 kg / m3).
47.40.Ki Supersonic and hypersonic flows
$^1$Department of Molecular Processes and Extreme Matter States, Faculty of Physics, M.V. Lomonosov Moscow State University.