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<p>The reliable initiation of oblique detonation waves (ODWs) represents a critical factor determining the operational performance of oblique detonation engines (ODEs). While previous research has predominantly focused on idealized semi-infinite wedge configurations, such studies have consistently revealed challenges including wave instability, detonation quenching, and compromised engine efficiency. This study presents a numerical investigation of initiation mechanisms and flow field characteristics in ODWs induced by curved surfaces. The analysis employs two-dimensional, multispecies, compressible Reynolds-averaged Navier-Stokes equations coupled with a detailed acetylene combustion model. Key results demonstrate that curved-surface-induced detonations achieve a substantially wider standing range than wedge-induced counterparts, primarily attributable to sustained compression effects generated by concave geometries. Notably, at small wedge angles, the curved surface configuration significantly reduces the detonation initiation distance. The initial formation phase reveals unstable behavior characterized by the large-angle overdriven detonation wave originating from the downstream steep wall section, which subsequently migrates upstream before stabilizing. Detailed examination of the wave structure identifies four distinct components: a curved shock wave (CSW), an overdriven detonation front, a transmitted shock wave, and a supersonic jet flow. Within this configuration, we observe an alternating reflection pattern of expansion waves and compression waves in the supersonic jet region, arising from Type IVr shock-shock interactions between the overdriven detonation wave and the CSW. Viscous effects analysis shows that the gradual curvature transition between the wall and flat plate effectively attenuates shock wave/boundary layer interactions. Furthermore, increased boundary layer thickness is found to significantly alter the ODW morphology while simultaneously inhibiting upstream propagation of the downstream overdriven detonation wave. These findings provide fundamental insights into the complex fluid dynamics governing ODEs, offering valuable implications for the development of more stable and efficient propulsion systems.</p>

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Study on the initiation characteristics of oblique detonation waves induced by curved surfaces in acetylene-air mixtures

  • 期刊论文

  • 发表日期：

    2026年3月13日

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  • Yirong Xin,
  • Gaoxiang Xiang,
  • Yichen Zhang,
  • Qiu Wang

摘要

The reliable initiation of oblique detonation waves (ODWs) represents a critical factor determining the operational performance of oblique detonation engines (ODEs). While previous research has predominantly focused on idealized semi-infinite wedge configurations, such studies have consistently revealed challenges including wave instability, detonation quenching, and compromised engine efficiency. This study presents a numerical investigation of initiation mechanisms and flow field characteristics in ODWs induced by curved surfaces. The analysis employs two-dimensional, multispecies, compressible Reynolds-averaged Navier-Stokes equations coupled with a detailed acetylene combustion model. Key results demonstrate that curved-surface-induced detonations achieve a substantially wider standing range than wedge-induced counterparts, primarily attributable to sustained compression effects generated by concave geometries. Notably, at small wedge angles, the curved surface configuration significantly reduces the detonation initiation distance. The initial formation phase reveals unstable behavior characterized by the large-angle overdriven detonation wave originating from the downstream steep wall section, which subsequently migrates upstream before stabilizing. Detailed examination of the wave structure identifies four distinct components: a curved shock wave (CSW), an overdriven detonation front, a transmitted shock wave, and a supersonic jet flow. Within this configuration, we observe an alternating reflection pattern of expansion waves and compression waves in the supersonic jet region, arising from Type IVr shock-shock interactions between the overdriven detonation wave and the CSW. Viscous effects analysis shows that the gradual curvature transition between the wall and flat plate effectively attenuates shock wave/boundary layer interactions. Furthermore, increased boundary layer thickness is found to significantly alter the ODW morphology while simultaneously inhibiting upstream propagation of the downstream overdriven detonation wave. These findings provide fundamental insights into the complex fluid dynamics governing ODEs, offering valuable implications for the development of more stable and efficient propulsion systems.