Heat flux measurement of Apollo capsule model in the free-piston shock tunnel HIEST
Heat flux measurement of Apollo capsule model in the free-piston shock tunnel HIEST
复制标题
自由活塞激波风洞中 Apollo 太空舱模型的热通量测量 HIEST
DOI：
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发表时间：
2009
期刊：
影响因子：
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通讯作者：
Eiichiro Nakano
中科院分区：
文献类型：
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作者：
H. Tanno;T. Komuro;Kazuo Sato;K. Itoh;Tetsuya Yamada;Naoki Sato;Eiichiro Nakano
本文介绍了在日本宇宙航空研究开发机构Kakuda的自由活塞激波隧道HIEST中，在高焓流条件下对阿波罗太空舱模型进行气动加热的最新测试结果。目的是获得基准数据，以验证JAXA内部数值模拟代码，这些代码用于预测超高速流场，例如再入飞行器周围的外部流。su -304不锈钢模型的最大直径为250毫米，迎风表面配备了84个微型同轴热电偶。在模型的背风侧还安装了12个热电偶，用于确定模型周围流动的建立。测量了高焓高压（即高雷诺数）在0和300攻角下模型周围的热流密度分布。在全层流边界层和过渡边界层条件下观察到气动加热特性。为了改变自由流雷诺数，将滞止压力从14 MPa变化到54 MPa，将滞止焓从3.6 MJ/kg变化到21 MJ/kg。讨论了高焓高压喷枪用石墨喷管喉部的流动特性。
This report presents the latest test results on the aeroheating of an Apollo capsule model under high-enthalpy flow conditions in the free-piston shock tunnel HIEST at JAXA Kakuda. The objective was to obtain benchmark data to validate JAXA in-house numerical simulation codes developed to predict hypervelocity flow fields such as the external flow around a re-entry vehicle. The SUS-304 stainless steel model had a maximum diameter of 250 mm and was equipped with 84 miniature co-axial thermocouples on its windward surface. Twelve thermocouples were also mounted on the leeward side of the model and were used to determine the establishment of flow around the model. Heat flux distribution around the model was measured in a high-enthalpy, high-pressure (i.e. high Reynolds number) flow at 0o and 30o angles of attack. Aeroheating characteristics were observed with a fully laminar boundary layer and with a transition boundary layer. To change the free-stream Reynolds number, stagnation pressure was varied from 14 MPa to 54 MPa and stagnation enthalpy was varied from 3.6 MJ/kg to 21 MJ/kg. The flow characteristics of the graphite nozzle throat, which was designed for high-enthalpy, high-pressure shots, are also discussed.