Efficiency of Detonation Combustion of Kerosene Vapor in Nozzles of Various Configurations

Using the methods of computational fluid dynamics, a comparative analysis of the stabilization of the detonation combustion of kerosene vapor in a supersonic air flow entering an expanding and convergent-divergent axisymmetric nozzle with a central body is carried out. The mathematical model is built based on unsteady two-dimensional Euler equations for the axisymmetric flow of a multicomponent reacting gas and a reduced detailed scheme of the chemical kinetics of ignition and combustion of a kerosene mixture. The calculations use a modification of the numerical scheme of S.K. Godunov of the second order of approximation of smooth solutions in space variables. The configurations of the nozzle channels which stabilize the de-tonation combustion of kerosene vapor are determined. Under conditions of the surface atmosphere, the efficiency of detonation combustion of kerosene in an expanding nozzle and a convergent-divergent nozzle is compared in terms of the specific impulse and thrust at Mach numbers of the oncoming flow of 7 and 9.