论文标题
通用高超音速入口流动的航空特征的预测
Prediction of aerothermal characteristics of a generic hypersonic inlet flow
论文作者
论文摘要
对于高速飞行车辆的设计，准确的航空表面载荷预测至关重要。在这项工作中，我们考虑了双投资几何形状上的超声流的数值解，这是空气呼吸飞行车辆入口的代表，其特征是在8.3时以三维相交的冲击波/湍流边界互动。高雷诺数（$ re_l \ \ $ re_l \约11.6 \ times 10^6 $基于自由流条件）和冷墙的存在（$ t_w/t_o \ of约0.27 $），从而导致近壁温度梯度必须使用壁模型的大型模拟（WMLE），以便进行计算，以进行计算。 WMELS结果与实验测量结果的比较显示了在时间平均的表面热通量和壁压分布中的良好一致性，而WMLES预测显示，相对于实验测量，比先前的计算相对于实验测量值降低。尽管存在许多非平衡条件，包括三维，冲击 - 边界层相互作用和流动分离，但使用基于平衡边界层近似的LES壁模型获得了有利的比较。最后，还证明，在LES壁模型中使用半本地涡流尺度（代替常用的货车最干燥的缩放）对于准确预测表面压力载荷和热量通量是必要的。
The accurate prediction of aerothermal surface loading is of paramount importance for the design of high speed flight vehicles. In this work, we consider the numerical solution of hypersonic flow over a double-finned geometry, representative of the inlet of an air-breathing flight vehicle, characterized by three-dimensional intersecting shock-wave/turbulent boundary-layer interaction at Mach 8.3. High Reynolds numbers ($Re_L \approx 11.6 \times 10^6$ based on free-stream conditions) and the presence of cold walls ($T_w/T_o \approx 0.27$) leading to large near-wall temperature gradients necessitate the use of wall-modeled large-eddy simulation (WMLES) in order to make calculations computationally tractable. The comparison of the WMLES results with experimental measurements shows good agreement in the time-averaged surface heat flux and wall pressure distributions, and the WMLES predictions show reduced errors with respect to the experimental measurements than prior RANS calculations. The favorable comparisons are obtained using an LES wall model based on equilibrium boundary layer approximations despite the presence of numerous non-equilibrium conditions including three dimensionality, shock-boundary layer interactions, and flow separation. Lastly, it is also demonstrated that the use of semi-local eddy viscosity scaling (in lieu of the commonly used van Driest scaling) in the LES wall model is necessary to accurately predict the surface pressure loading and heat fluxes.
