Abstract:
The problem of propagation of a plane detonation wave is studied on the basis of a mathematical model for the detonation of aluminum particles in oxygen with allowance for the difference in velocities and temperatures of components. A qualitative analysis of the final steady state is performed. The domains of existence of steady solutions and the manifold of solutions of various types are determined. Various types of flows are illustrated numerically. The special features of the flow structure behind the front are analyzed, depending on relaxation parameters. We have performed flow calculations taking into account the characteristic times versus the parameters behind the front and have shown agreement between the data obtained and the frozen and variable relaxation parameters. The data obtained are found to correspond to the known experimental results concerning the widths of the ignition and combustion zones.
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