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首页> 外文会议>AIAA Aerospace Sciences Meeting;AIAA SciTech Forum >DSMC Computations of Separation over a 'Tick' model in Hypersonic High Enthalpy Transitional Flows
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DSMC Computations of Separation over a 'Tick' model in Hypersonic High Enthalpy Transitional Flows

机译：高超声速高焓过渡流中“滴答”模型分离的DSMC计算

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The shock-wave boundary layer interaction and separation characteristics concerning the flow over a leading edge separated flow configuration, also known as a 'tick' configuration, is numerically studied in this paper. The flow domain spans localized areas from rarefied to continuum regimes, evolving from a combination of expansion and compression processes. The computations are performed using a Direct Simulation Monte Carlo code developed by Sandia Laboratories, called SPARTA. An extensive convergence study is taken to quantify the numerical error levels in the results and is found to be within 9% relative to a model with infinitesimally small time step and cell-sizes. A theoretical sharp leading edge model is computed first to identity the distinct flow features and separation phenomena. An incipient separation behavior was observed for this case. Two collision schemes, one based on the traditional random selection of collision partners and the other based on a Near Neighbor approach, are evaluated for a gas mixture comprising species with significant mass differences. The relative deviation in velocity slip, between the two schemes, is found to be higher than the magnitude of error levels. Also, the effect of leading edge bluntness are evaluated at a radius of 0.01mm, 0.03mm and 0.1mm. The increase in bluntness is found to have significant effect on the surface quantities and separation size. The effect of limited equilibration of incident molecules to the surface temperature is evaluated by comparing accommodation coefficients of 1 and 0.75. The effect is more pronounced for the largest bluntness radius of 0.1mm, for which the separation and re-attachment locations are both displaced downstream by 5-6% for the accommodation coefficient of 0.75 relative to full accommodation.
机译：本文通过数值研究了与前沿分离流动形态（也称为“滴答”形态）上的流动相关的激波边界层相互作用和分离特性。流动域跨越了局部区域，从稀疏状态到连续介质状态，是由膨胀和压缩过程的组合演变而来的。使用桑迪亚实验室开发的称为SPARTA的直接模拟蒙特卡洛代码执行计算。进行了广泛的收敛研究以量化结果中的数字误差水平，相对于具有无限小的时间步长和像元大小的模型，发现误差在9％以内。首先计算理论上的尖锐前沿模型，以识别不同的流动特征和分离现象。在这种情况下观察到初期分离行为。针对包含质量差异显着的物质的混合气体，评估了两种碰撞方案，一种基于传统的随机选择碰撞伙伴，另一种基于近邻方法。发现这两种方案之间的速度滑移的相对偏差大于误差水平的大小。同样，在半径为0.01mm，0.03mm和0.1mm的情况下评估前缘钝化的影响。发现钝度的增加对表面量和分离尺寸具有显着影响。通过比较1和0.75的调节系数，可以评估入射分子对表面温度的有限平衡的影响。对于最大钝角半径为0.1mm的效果更为明显，对于0.75的调节系数，相对于完全调节而言，分离位置和重新连接位置均向下游位移了5-6％。

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