Abstract:

Under low Mach number flight conditions， oblique detonation engines face the inherent contradiction between reliable initiation and flow pressure loss. Smaller wedge angles prove insufficient to achieve stable detonation initiation， while larger wedge angles induce excessive total pressure dissipation. To address this trade-off， this study introduces energy deposition ignition technology to investigate how single-pulse ignition affects oblique detonation wave initiation and combustion stabilization. Incorporating wall viscous effects， numerical simulations are conducted through detailed chemical reaction modeling and unsteady Navier-Stokes equations resolution. The results demonstrate that single-pulse ignition effectively induces detonation wave initiation and maintains self-sustained combustion under specific conditions. Evolution analysis of oblique detonation waves under varying ignition source heights reveals that excessively elevated ignition positions prevent effective coupling between flame fronts and leading shock waves， resulting in initiation failure. Comparative analysis between inviscid and viscous flows unveils the underlying stabilization mechanism： the interaction between the strong transverse waves triggered by single-pulse ignition and the boundary layer induces a stable recirculation zone， which serves as the core physical mechanism for achieving detonation re-initiation and long-term stabilization.

Key words: hypersonic, oblique detonation wave, energy deposition ignition, boundary layer, detonation initiation