Application of gas-kinetic scheme with kinetic boundary conditions in hypersonic flow
Application of gas-kinetic scheme with kinetic boundary conditions in hypersonic flow
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DOI：
10.2514/1.14130
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发表时间：
2005-10-01
期刊：
影响因子：
2.5
通讯作者：
Xu, K
中科院分区：
文献类型：
--
作者：
Li, QB;Fu, S;Xu, K
本文研究了基于Bhatnagar-Gross-Krook粒子碰撞模型的气体动力学格式在高超声速绕流数值模拟中的应用。构造并实现了具有不同调节系数的动力学边界条件。数值研究的基础上，层流激波/边界层的相互作用，在马赫数10流通过一个空心圆柱火炬模型。与网格无关的数值计算结果与实验测量结果吻合良好。动力学滑移边界条件的利用是必要的，以提高目前的结果，实验测量，以及直接模拟Monte Carlo解决方案之间的协议。定量地评价了调节系数的变化对流动解的影响。
This work focuses on the application of the gas-kinetic scheme based on the Bhatnagar-Gross-Krook particle collision model in the hypersonic flow simulations. Kinetic boundary conditions with different accommodation coefficients are constructed and implemented in the scheme. The numerical study is based on a laminar shock-wave/boundary-layer interaction in a Mach 10 flow passing through a hollow cylinder flare model. The grid-independent numerical results agree well with experimental measurements. The utilization of the kinetic slip boundary condition is necessary to improve the agreement between the current results, experimental measurements, as well as direct simulation Monte Carlo solutions. The effect of the variation of the accommodation coefficient on-the flow solutions is quantitatively evaluated.