| Abstract: | The flow of igniting hydrogen-air mixtures entering an axisymmetric convergent-divergent nozzle at a supersonic velocity is
considered. A possibility of stabilizing detonation combustion is numerically investigated at different freestream Mach numbers
with account for nonuniform distribution of hydrogen concentration at the nozzle entry. The investigation is performed on
the basis of the two-dimensional gasdynamic Euler equations for a multicomponent reacting gas. A detailed model of chemical
reactions is used. The calculated thrust is compared with the drag of a conical housing containing the supersonic nozzle considered. |
