Numerical study of continuously rotating detonation in two-fuel gaseous mixture

Abstract Numerical simulation of continuously rotating detonations stoichiometric two-fuel mixture with air has been carried out for the cylindrical annular detonation chamber (DC) rocket-type engine. The syngas (1-α)СO+αH2, a binary hydrogen H 2 and carbon monoxide CO, is taken. We studied global flow structure in DC, detailed transverse wave (TW) front continuous regime. Integral characteristics process − distribution average values static total pressure along length value specific impulse have obtained. region existence stable regime coordinates stagnation - temperature injection manifold (receiver) geometric limit TW determined.