Continuous detonation in a supersonic flow of a hydrogen-oxygen mixture
Source abstract
Abstract
The problem of continuous spin detonation in a supersonic flow in a flow-type annular combustor is considered in a two-dimensional unsteady formulation. The dynamics of the detonation wave in a hydrogen-oxygen mixture with isentropic and shock-wave compression of the flow in the input diffuser is studied. It is shown that the mass flow rate of the mixture through the combustor decreases as continuous spin detonation is formed, and a steady regime with a “detached” shock wave is observed at the entrance of the supersonic diffuser. For a contoured combustor, the limit from above is obtained for the Mach number of the incoming supersonic flow at which a continuous detonation regime is obtained.
Source: openalex_inverted_index · Quality: baseline
Research context
OpenAlex topics: Combustion and Detonation Processes · Computational Fluid Dynamics and Aerodynamics · Combustion and flame dynamics
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (20)
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