Detached-Eddy Simulations of Hypersonic Capsule Wake Flow
Detached-Eddy Simulations of Hypersonic Capsule Wake Flow
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DOI：
10.2514/1.j052771
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发表时间：
2015
期刊：
影响因子：
2.5
通讯作者：
Joseph M. Brock;P. Subbareddy;G. Candler
中科院分区：
文献类型：
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作者：
Joseph M. Brock;P. Subbareddy;G. Candler
在猎户座载人飞船的球形舱模型上进行了数值模拟，并与布法罗Calspan大学研究中心获得的实验数据进行了比较。流速为6.4马赫，考虑迎角为28度的情况。我们感兴趣的是在存在大量分离和由此产生的高度不稳定尾流的情况下对后体加热的预测。采用多种通量格式对该流场进行了分离涡模拟，并考虑了网格细化的影响。计算结果与实验数据进行了对比，得到了后体分离部分的平均换热和波动换热。提出了瞬时流动特征的比较，以说明不同水平的解决尺度。
Numerical simulations are performed on a spherical capsule model based on the Orion Crew Exploration Vehicle and compared to experimental data obtained at the Calspan University of Buffalo Research Center. The flow is at Mach 6.4, and a case with an angle of attack of 28 deg is considered. The interest is in predictions of afterbody heating in the presence of massive separation and the resultant highly unsteady wake flow. Detached-eddy simulations of this flowfield are done using several flux schemes, and the effect of mesh refinement is considered. The results are compared to experimental data for mean and fluctuating heat transfer in the separated portion of the afterbody. Comparisons of instantaneous flow features are presented to illustrate varying levels of resolved scales.