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[交流] 【文章推荐】高超声速飞行地面测试的理论与技术（力学所姜宗林研究员）

文章题目：Theories and technologies for duplicating hypersonic flight conditions for ground testing

文章链接（免费获取，欢迎点击下载！）：https://doi.org/10.1093/nsr/nwx007

高超声速飞行气体动力学与亚声速和超声速气体动力学截然不同。对用于高超声速飞行的吸气式发动机（冲压发动机）进行地面测试非常困难，而飞行测试则非常昂贵。由力学所姜宗林研究员等人撰写的这篇 NSR Perspective 文章，对高超声速飞行地面测试的理论和技术进行了详细的介绍和探讨。

文章节选：
To carry out a reliable ground test at hypersonic Mach numbers, there are four key parameters required for hypersonic test facilities. The first parameter is the test gas and it is the key issue to ensure correct thermochemistry in test flows. The second is the total flow pressure and temperature with which the altitude pressure and temperature, and the flight speed can be reproduced with the proper nozzle expansion. Consequently, the chemical-reaction process can be simulated correctly, as well as the aerodynamic forces and momentum. The third is the nozzle size. In other words, the nozzle exit must be big enough to accommodate a large vehicle model so that the chemical-reaction time scale can be much smaller than that of the test gas flowing past the model. The last one is the test duration. For air-breathing hypersonic vehicles, the airframe is also part of the scramjet engine; therefore, the test duration has to be long enough to sustain stable supersonic combustion in the engine. Qian estimated the requirement and suggested that a 100-ms test time is sufficient for supersonic combustion research. Actually, there is a balance point for creating the test duration as long as the facility is not seriously damaged because of extremely high total temperature that causes a severe thermal barrier on the hypersonic wind tunnel. It is even more challenging that one has to simulate all these four parameters simultaneously in a single test facility, and it is the reason why there is still no single ground-based facility capable of duplicating the hypersonic flight environment after the 50 years of development of advanced hypersonic test facilities. Over recent decades, different facilities have been developed to address various aspects of the design problems associated with hypersonic flight. This idea works and a lot of experimental data are generated, but uncertainness and low accuracy are imposed on these wind-tunnel test data, resulting in slow development of hypersonic vehicles.

【文章图】驱动段和试验段末端气体分布的时间序列（白色：驱动气体；黑色：试验气体）

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