PENETRATION OF A SHOCK WAVE IN A FLAME FRONT

Abstract

The present paper deals with the interactions between a fully supersonic flame front, situated in a supersonic twodimensional flow of an ideal homogeneous combustible gas mixture, and an incident shock wawe, which is penetrating in the space of the hot burnt gases. A possible configuration, which was named ,,simple penetration” is examined. For the anlysis of the interference phenomena, shock polar and shock-combustion polar are used. At the same time, the paper shows the possibility to produce similar but more complicated configurations, which may contain expansion fans and reflected shock waves. M Notation i or j − subscrips indicating the i or j areas of the flow, ij − subscript for function or variable at the boundary among the two jointed areas, Mi − Mach number Ti − absolute temperature, γ − specific heat ratio, Q − heat liberated by chemical reactions per unit mass of the gas mixture, ai − sound velocity in the i area, pi − pressure ρi − density mi − flame Mach number, δij − deflection angle of the flow behind the flame front (or shock wave) between the i and j areas, R − gas constant,