Design and transition characteristics of a standard model for hypersonic boundary layer transition research

To understand fundamental problems in hypersonic laminar-turbulent boundary layer transition for three-dimensional complex vehicles,a new standard model with typical lifting-body features has been proposed,named as hypersonic transition research vehicle(HyTRV).The configuration of HyTRV is fully analytical,and details of the design process are discussed in this study.The transition characteristics for HyTRV are investigated using three combined methods,i.e.,theoretical analyses,numerical simulations,and wind tunnel experiments.Results show that the fully analytic parameterization design of HyTRV can satisfy the model simplification requirements from both numerical simulations and wind tunnel experiments.Meanwhile,the flow field of HyTRV reveals typical transition mechanisms in six relatively separated regions,including the streamwise vortex instability,crossflow instability,secondary instability,and attachment-line instability.Therefore,the proposed HyTRV model is valuable for fundamental researches in hypersonic boundary layer transition.

基于转捩模型的HyTRV外形转捩特性与攻角影响分析

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。