| 高超音速进气道的冷却研究 |
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| 引用本文： | 顾维藻,刘长春,涂建平,神家锐.高超音速进气道的冷却研究[J].工程热物理学报,1994(2). |
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| 作者姓名： | 顾维藻 刘长春 涂建平 神家锐 |
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| 作者单位： | 中科院工程热物理研究所 |
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| 摘 要： | 作为我国航天飞机研究的一个开端，本文以美国ＮＡＳＡ高超音速研究发动机ＨＲＥ的进气道几何为模型，进行了飞行马赫数为６时的进气道各部分的气动和气动热计算，并在此基础上提出了以氢燃料作冷却剂的主动冷却结构，进行了冷却计算，证明提出的冷却结构所需要的氢用量是合理的。
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| 关 键 词： | 进气道，气动热，强化冷却 |
STUDY OF COOLING FOR HYPERSONIC INLET |
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| Gu Weizao, Liu Changchun, Tu Jingping, Shen Jiarui.STUDY OF COOLING FOR HYPERSONIC INLET[J].Journal of Engineering Thermophysics,1994(2). |
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| Authors: | Gu Weizao Liu Changchun Tu Jingping Shen Jiarui |
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| Abstract: | As an initiation for the study of aerospace aircraft, in this article aerothermodynamic prediction of hypersonic inlet was presented. Based on the predicted distribution of heat flux the enhanced cooling method for the inlet casing, central cylinder and its front cone were suggested. Prediction results showed that the required quantity of hydrogen for the active cooling of stainless steel inlet will be below 0.4 kg/s. |
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| Keywords: | inlet aerodynamic heating enhanced cooling |
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