Kerosene combustion in a pseudoshock with varied conditions at the scramjet combustor model

Results of studying kerosene combustion in a pseudoshock with varied temperature and velocity at the scramjet combustor model are presented. Thermodynamic estimates show that either a supersonic or transonic flow can be retained over the combustor duct at parameters corresponding to the Mach number at the engine entrance $\mathrm{M}_0\approx4.5$. The possibility of the pseudoshock regime in the constant-section part of the combustor is experimentally studied in the case where the Mach number behind the inlet (at the combustor entrance) is $\mathrm{M}_c>1$. Conditions of initiation and evolution of this combustion mode under a pulsed-periodic action on the flow are determined.