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 convergentdivergent 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 detonation 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 $9$.