对于高超声速飞行器，边界层转捩引起的表面热流突升、气动阻力系数增大、进气道流量变化等是影响飞行计划成功与否的关键问题，因此有必要对高超声速边界层转捩现象进行深入研究。采用改进的k⁃ω⁃γ转捩模型对高超声速转捩研究飞行器HyTRV的转捩特征进行了数值模拟，并将数值计算结果与风洞试验结果进行了对比，验证了转捩模型对HyTRV外形的转捩现象具有较好的预测能力。在此基础上，对HyTRV外形的转捩特征进行了研究，发现HyTRV外形迎风面、背风面存在流向涡、第二模态、横流模态3种扰动失稳诱导的边界层转捩；分析了不同攻角下HyTRV外形转捩阵面分布规律，发现当来流攻角增大，迎风面上的流向涡被压扁，背风面腰部位置的流向涡向顶部移动，流向涡的变形、移动导致转捩阵面发生变化，并出现了不同转捩区域融合的现象。研究结果不仅揭示了HyTRV外形随攻角变化的规律，而且展示了改进的k⁃ω⁃γ转捩模型在处理复杂飞行器外形问题时的巨大应用潜力，为深入探究复杂飞行器边界层转捩现象提供了一种有效的分析工具。

For hypersonic vehicles， certain issues are crucial to the success of flight plans， including sudden increase in surface heat flux， rising aerodynamic drag coefficients， and changes in intake airflow caused by boundary layer transition. Therefore， conducting in-depth research into boundary layer transition phenomena at hypersonic speeds is imperative. An improved k-ω-γ transition model is utilized to numerically simulate the transition characteristics of the Hypersonic Transition Research Vehicle （HyTRV）. Firstly， the results of the baseline condition of the HyTRV obtained with the improved k-ω-γ transition model are compared with the results of wind tunnel test， affirming that the transition model possesses a good predictive capability for the transition phenomenon of the HyTRV configuration. Then， the transition properties of the HyTRV configuration are analyzed， disclosing the existence of streamwise vortex instability， secondary instability， and cross-flow instability on HyTRV to induce boundary layer transitions. Finally， different transition configurations of HyTRV at various angles of attack are investigated. As the angle of attack increases， the streamwise vortex on the windward surface becomes compressed， and the streamwise vortex on the leeward surface moves upward. The deformation and movement of the streamwise vortex lead to changes in the transition configurations， which results in the merging of different transition areas. This research not only reveals the pattern of changes in the HyTRV’s shape with varying angles of attack， but also demonstrates the significant application potential of the improved k-ω-γ transition model in addressing complex shapes of hypersonic vehicles. It offers an effective analytical tool for in-depth exploration of boundary layer phenomena in complex vehicles.