The oblique detonation engine (ODE)-based aircraft employs the fast oblique detonation wave (ODW) combustion for airbreathing propulsion, delivering significant technical advantages in structure and efficiency under hypersonic flight conditions. However, achieving overall optimization by harmoniously integrating the ODE internal flows with the aircraft external flows remains a crucial yet unexplored aspect. Utilizing a multi-species reactive Reynolds-Averaged Navier-Stokes (RANS) model along with a detailed hydrogen-air combustion mechanism, an integrated airframe-propulsion ODE aircraft model is developed to investigate the internal/external flow and thrust-drag characteristics of an ODE aircraft operating at a flight Mach number of 10. Simulation results demonstrate the two key aerodynamic and geometric design parameters, i.e., inlet exit Mach numbers and combustor wedge angles , exhibit inverted U-shaped curve effects on ODE specific impulse . The optimal configurations with = 5 and = 20° are identified as the most effective balance for ODE performance, achieving the maximum of about 1200s. The underlying mechanisms are elucidated from the viewpoints of variations in both combustion efficiency and total pressure. Furthermore, a slightly different inlet exit Mach number of = 5.5 is found to achieve the maximum flight efficiency by reducing the flight drag, indicting the thrust-drag trade-off in ODE aircraft optimal design. This study provides a comprehensive understanding of the significance of balancing propulsion and aerodynamic performance for ODE aircraft to achieve superior overall performance, which holds the key to future engineering applications.

中文翻译：

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斜爆发动机飞行器内外流及推阻特性数值研究


基于斜爆轰发动机（ODE）的飞机采用快速斜爆震波（ODW）燃烧进行吸气式推进，在高超声速飞行条件下在结构和效率上具有显着的技术优势。然而，通过协调集成 ODE 内部流与飞机外部流来实现整体优化仍然是一个关键但尚未探索的方面。利用多物种反应雷诺平均纳维斯托克斯 (RANS) 模型以及详细的氢气-空气燃烧机制，开发了一种集成机身推进 ODE 飞机模型，用于研究飞机的内部/外部流动和推力阻力特性ODE 飞机的飞行马赫数为 10。仿真结果表明，两个关键的空气动力学和几何设计参数，即入口出口马赫数和燃烧室楔角，对 ODE 比冲呈现倒 U 形曲线效应。 = 5 和 = 20° 的最佳配置被认为是 ODE 性能的最有效平衡，可实现约 1200 秒的最大值。从燃烧效率和总压力的变化的角度阐明了潜在的机制。此外，发现入口出口马赫数 = 5.5 略有不同，可以通过减少飞行阻力来实现最大飞行效率，这表明 ODE 飞机优化设计中的推力-阻力权衡。这项研究全面了解了平衡推进力和气动性能对于ODE飞机实现卓越整体性能的重要性，这对未来工程应用至关重要。