Abstract
The scramjet engine is the key component for high-speed transportations. In the present paper, the DLR scramjet combustor’s performance under a non-reacting flow field is numerically studied. The computational study has been performed using the commercial code ANSYS 18.0 software. The Reynolds averaged Navier Stokes (RANS) equations and the shear stress transport (SST) k-ω turbulence models are used to model the study. The numerical results are validated with the reported experimental data and are in compliance within the range for further investigation. The combustor’s performance with different geometry profiles is compared with the DLR scramjet model in numerical shadowgraph images, wall pressures, static mid-pressures and total pressure loss across the combustor. The numerical shadowgraph images show the flow field characteristics such as shock patterns, the shock to shear layer interactions and shock–shock interaction.
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