Abstract
Numerical simulation of continuously rotating detonations of stoichiometric two-fuel mixture with air has been carried out for the cylindrical annular detonation chamber (DC) of the rocket-type engine. The syngas (1−α)CO+αH2, a binary mixture of hydrogen H2 and carbon monoxide CO, is considered as a fuel. The global §ow structure in the DC and the detailed structure of the transverse detonation wave front in the continuous rotating regime have been studied. Integral characteristics of the detonation process ¡ the distribution of average values of static and total pressure along the length of the DC and the value of speci¦c impulse at the DC exit ¡ have been obtained. The regions of existence of stable continuous rotating detonation regime in coordinates ¤stagnation pressure pm stagnation temperature Tm¥ in injection manifold (receiver) have been determined. The minimal values of the DC length and radius for stable rotating detonation for some regions at the pm Tm plane have been found.
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