Abstract
The cavity flame holder is a conventional technique for efficient fuel mixing and auto-ignition inside the Scramjet engine. In this study, a computational method is applied to study the impact of the wedge shock generator on the fuel mixing performance inside the combustor at the supersonic flow of M=4. The main focus of the current work is to compare the vortex structure formed inside the cavity in various conditions. To perform simulations, a three-dimensional model with a structure grid is produced to fine reliable solution for our study. To capture the real flow structure, the SST turbulence model is applied for obtaining viscosity. The obtained results demonstrate that the presence of the wedge shock generator increase the mainstream entrains into the cavity. This declines the temperature inside the cavity and strengthens the fuel mixing rate which is highly significant for the efficient combustion process within the scramjet engine. According to our findings, secondary circulation weakens by the amplification of the oblique shock.
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