| Abstract: | The results of the experimental investigation of the flow in the vicinity of an electric-discharge module having a low aerodynamic
drag and intended for igniting hydrocarbon fuel and stabilizing its burning in a supersonic flow at low initial static temperature
and pressure are presented. The distinctive feature of the module is that the combustion zone is not attached to the combustion
chamber walls. Due to a certain geometric connection between different regions of the module anode, an interference of shock
and expansion waves occurs in its vicinity. This leads to the formation of a local longitudinal low-pressure zone behind the
anode, the convergence of individual fuel jetlets injected through orifices in the anode in this zone, the formation precisely
there of a longitudinal nonequilibrium discharge, and the intensification of fuel mixing and plasmochemical reactions. The
gasdynamic features of supersonic flow past the module are numerically investigated. The dynamics of electrical discharge
formation and the combustion zones thus formed are studied under particular conditions. The data on the stagnation temperature
distribution in the discharge wake are obtained. |
