Simulation of blunt-fin-induced shock-wave and turbulent boundary-layer interaction
Simulation of blunt-fin-induced shock-wave and turbulent boundary-layer interaction
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DOI：
10.1017/s0022112085001471
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发表时间：
1985-05
影响因子：
3.7
通讯作者：
C. Hung;P. Buning
中科院分区：
文献类型：
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作者：
C. Hung;P. Buning
数值求解了雷诺平均的Navier-Stokes方程，计算了超音速绕平板钝体尾翼的流动。翅片激波导致边界层分离，从而产生复杂的三维激波和边界层相互作用。计算结果与翅片和平板上测得的平均静压力吻合较好。对翅片前缘压力峰值和平板双峰等主要特征进行了较好的预测。讨论了马蹄涡的作用。这种旋涡导致高速流动的发展，从而导致翅片和平板上的低压区域。对不同厚度的入射边界层进行了研究。改变厚度一个数量级表明，马蹄涡的大小和相互作用的空间范围是由无粘流主导的，仅与雷诺数有微弱的关系。彩色图形用来显示相互作用流场的细节。
The Reynolds-averaged Navier–Stokes equations are solved numerically for supersonic flow over a blunt fin mounted on a flat plate. The fin shock causes the boundary layer to separate, which results in a complicated, three-dimensional shock-wave and boundary-layer interaction. The computed results are in good agreement with the mean static pressure measured on the fin and the flat plate. The main features, such as peak pressure on the fin leading edge and a double peak on the plate, are predicted well. The role of the horseshoe vortex is discussed. This vortex leads to the development of high-speed flow and, hence, low-pressure regions on the fin and the plate. Different thicknesses of the incoming boundary layer have been studied. Varying the thicknesses by an order of magnitude shows that the size of the horseshoe vortex and, therefore, the spatial extent of the interaction are dominated by inviscid flow and only weakly dependent on the Reynolds number. Coloured graphics are used to show details of the interaction flow field.