Abstract
Abstract The results of numerical investigation of thermogasdynamics of a model scramjet combustion chamber with an ethylene flameholder made in form of an asymmetric trapezoidal cavity are given. The regimes of supersonic air flow at the combustion chamber inlet are studied at the Mach number 2.2, the pressure 0.416–1 atm, and the total ethylene flow rate of the order of 10 g/(s cm) through two injectors located in the cavity. A two-dimensional computational model based on the system of time-dependent Navier–Stokes equations, the energy conservation and continuity equations for the gas mixture and individual chemical components, as well as the system of chemical kinetics, is used. The spectral and integral radiative heat fluxes towards the chamber walls were calculated using the thermal radiation transfer equation. It is shown that in the calculated cases considered the density of convective heat flux towards the combustion chamber walls can reach 20 W/cm2 and the density of integral radiative heat fluxes is of ~1 W/cm2.
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