Shock waves generated by a pulsed surface sliding discharge in a supersonic airflow past a wedge

An experimental study was made of the dynamics of shock waves developing from a localized channel of a nanosecond surface sliding discharge in supersonic airflows past a wedge in the shock tube with Mach numbers 1.16-1.47 at a density of 0.02 kg/m(3)-0.20 kg/m(3). It is shown that a semi-cylindrical explosive-type shock wave is formed from the discharge channel in the low-density vortex zone behind the wedge. Numerical simulations of the resulting gas-dynamic flow are performed. The shadowgraphy images of shock waves after the discharge were compared with simulations of the flow field after an energy input near the wall in a supersonic flow. The energy input region in the simulations was set in accordance with the experimental results on the geometry of the discharge channel. Based on a comparison of experimental results and simulations, it is shown that shock waves are formed when a heat energy of 0.07 +/- 0.04 J is released in the channel of localized discharge in supersonic airflows.