LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition
LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition
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DOI：
10.2514/6.2015-0210
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发表时间：
2015-01
期刊：
影响因子：
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通讯作者：
T. Ishihara;Y. Ogino;N. Ohnishi;H. Tanno
中科院分区：
文献类型：
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作者：
T. Ishihara;Y. Ogino;N. Ohnishi;H. Tanno
开发了高阶 CFD 代码，用于高超声速流中湍流热通量的 LES 计算。在 JAXA 角田航天中心的自由活塞激波风洞 HIEST 上，对阿波罗太空舱模型和 JAXA 正在开发的载人太空舱 HTV-R 进行了强制过渡的空气加热测量测试。测量数据表明，阿波罗太空舱模型前体的热通量比层流大1.5-2倍。另一方面，HTV-R尾部的热通量明显变大。此外，在胶囊尾部存在的分离区域中，能够再现附着流中的湍流热通量的Baldwin-Lomax模型往往会被低估。为了通过数值模拟再现后体上的湍流热流，需要针对高超声速流中的 LES 的高阶 CFD 代码。由于高超声速流中的LES需要激波附近的鲁棒性和边界层的高分辨率，因此采用改进的WENO方法。我们计算了圆柱体周围的高超声速流动（M∞ = 17），并研究了该方法对强冲击的鲁棒性。获得了平滑的压力分布，与 NASA LAURA 代码计算的热通量非常吻合。我们开发的代码应用于 HTV-R 周围的高超音速流场，并检查了热通量。
A high order CFD code was developed for LES computation of turbulent heat flux in hypersonic flow. Aeroheating measurement tests with forced transition on an Apollo capsule model and an HTV-R which was a manned space capsule under development by JAXA were performed by the free-piston shock tunnel HIEST in JAXA Kakuda Space Center. Measured data set indicate that heat flux on the forebody of the Apollo capsule model was 1.5-2 times larger than one in laminar flow. On the other hand, the heat flux on the afterbody of HTV-R became significantly larger. Furthermore, in the separation region which exists afterbody of capsules, the Baldwin-Lomax model which can reproduce turbulent heat flux in the attached flow, tends to underestimate. In order to reproduce the turbulent heat flux on the after body by numerical simulation, high order CFD code towards LES in hypersonic flow is needed. Since the robustness near the shock and high resolution in the boundary layer is needed for LES in hypersonic flow, improved WENO method is employed. We calculated the hypersonic flow (M∞ = 17) around cylinder and investigated the robustness for strong shock by the method. Smooth pressure distribution was obtained agree well with the calculated heat flux by NASA LAURA code. Our developed code applied to the hypersonic flowfield around HTV-R with a trip and the heat flux was examined.