Detonative combustion offers significant thermodynamic advantages for high‑speed propulsion, motivating the development of detonation‑based combustors for hypersonic flight. Among these, oblique detonation wave (ODW) engines require extremely high combustor velocities to achieve steady wave stabilization. While most prior experimental and numerical studies have focused on planar two‑dimensional geometries, axisymmetric combustors offer practical benefits for hypersonic vehicle integration and ma