Abstract

To predict the boundary layer transition on swept wings, experimental and numerical researches were conducted to obtained the accurate boundary layer transition front and to evaluate the performance of two transition predicting models. Flow visualization and temperature measurement over a 65° swept wing were carried out under M = 6 with nano-tracer-based planar laser scattering system and temperature sensitive paints. Meanwhile, the k_T–k_L–ω and γ–Re_θt turbulence models were used to predict the boundary layer transition. Experiment results reflect that the transition front on the wing consists of three parts, including the transition near the wing root induced by separation, the transition dominated by stationary crossflow vortices and the transition in the connected region. The comparison between the simulation and experiment shows that the k_T–k_L–ω model performs better than γ–Re_θt model in predicting the shape and position of the transition front, as well as the limiting streamlines. Thus, the k_T–k_L–ω model is more suitable in predicting the boundary layer transition for this type of swept wing.

中文翻译：

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M=6时后掠翼边界层过渡前沿的实验与数值模拟研究

摘要

为了预测后掠翼边界层过渡，进行了实验和数值研究，以获得准确的边界层过渡前沿，并评估两种过渡预测模型的性能。使用基于纳米示踪剂的平面激光散射系统和温度敏感涂料在 M = 6 下进行 65° 后掠翼上的流动可视化和温度测量。同时，k _T –k _L – ω 和 γ–Re _θt湍流模型用于预测边界层转变。实验结果表明，机翼上的过渡锋由三部分组成，包括分离引起的翼根附近的过渡、静止横流涡主导的过渡和连通区域的过渡。仿真与实验的对比表明，k _T –k _L – ω模型在预测过渡前沿的形状和位置以及限制流线方面的性能优于 γ–Re _θt模型。因此，k _T –k _L – ω 模型更适合预测这种后掠翼的边界层转变。