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Starting characteristics and phenomenon of a supersonic wind tunnel coupled with inlet model

机译：进气道耦合的超音速风洞启动特性及现象

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摘要

Supersonic wind tunnel is regarded the most efficient experimental facility for studying the performance of supersonic inlets. In view of this background, the starting problem of a wind tunnel coupled with the inlet model is a critical experimental issue. However, inlet experiments cannot be performed when wind tunnels do not start. To satisfy this requirement, this study adopts numerical simulations to examine the starting characteristics of a wind tunnel coupled with the inlet model to serve as a basis for observing the flow at the starting procedure. Results of steady simulation show that the wind tunnel coupled with the medium-sized inlet model is still at risk in the starting procedure, although the inlet size of the model is considerably smaller than the physical limitation. Furthermore, imposing high total pressure on the wind tunnel inlet can make the wind tunnel restart. However, results also reveal that gradually increasing total pressure does not necessarily restart the wind tunnel, as wind tunnels can start only when total pressure amplitude is large enough. To improve the understanding of the phenomena, unsteady numerical simulations with different total pressure levels are performed on the wind tunnel inlet. Numerical results demonstrate the importance of generating a moving shock wave with adequate intensity that can overcome the structure of the separation zones near wind tunnel walls after sweeping the inlet model. Under this influence, the separation zones become relatively smaller, thereby weakening the intensity of the deduced shock wave. Several changes to improve the startup of the wind tunnel are also observed, such as the attachment of the detached shock wave mechanism situated in front of the inlet model and the disappearance of the shock wave/boundary-layer interactions near the lower wall. These changes can reduce total pressure loss in the wind tunnel and prompt the wind tunnel to restart. In conclusion, a sudden increase in total pressure can easily start the wind tunnel. The valve of the wind tunnel should therefore be opened rapidly regardless whether the wind tunnel is in the starting or non-starting procedure. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：超音速风洞被认为是研究超音速进气口性能的最有效的实验设备。鉴于此背景，与进气口模型耦合的风洞的启动问题是一个关键的实验问题。但是，当风洞不启动时，无法进行进气实验。为了满足这一要求，本研究采用数值模拟方法研究了风洞的启动特性，并结合了进气模型，以作为启动过程中观测流量的基础。稳定的模拟结果表明，尽管模型的进气口尺寸大大小于物理极限，但在启动过程中，风洞与中型进气口模型仍然处于危险之中。此外，在风洞入口上施加高的总压力会使风洞重启。但是，结果还表明，逐渐增加的总压力并不一定会重新启动风洞，因为只有在总压力幅度足够大时才能启动风洞。为了增进对现象的理解，在风洞入口处进行了具有不同总压力水平的非稳态数值模拟。数值结果表明，生成具有足够强度的移动冲击波的重要性，该冲击波可以在扫掠入口模型后克服风洞壁附近的分离区的结构。在这种影响下，分离区变得相对较小，从而削弱了推论出的冲击波的强度。还观察到了一些改善风洞启动的变化，例如位于进气口模型前面的分离式冲击波机制的附着以及下壁附近冲击波/边界层相互作用的消失。这些变化可以减少风洞中的总压力损失，并促使风洞重新启动。总而言之，总压力的突然升高很容易启动风洞。因此，无论风洞处于启动还是非启动过程中，都应迅速打开风洞的阀门。 （C）2018 Elsevier Masson SAS。版权所有。

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  • 来源
    《Aerospace science and technology》 |2018年第6期|626-637|共12页
  • 作者

    Yu Kaikai; Xu Jinglei; Liu Shun; Zhang Xiaofei;

  • 作者单位

    Nanjing Univ Aeronaut & Astronaut, Jiangsu Prov Key Lab Aerosp Power Syst, Nanjing 21006, Jiangsu, Peoples R China;

    Nanjing Univ Aeronaut & Astronaut, Jiangsu Prov Key Lab Aerosp Power Syst, Nanjing 21006, Jiangsu, Peoples R China;

    Nanjing Univ Aeronaut & Astronaut, Jiangsu Prov Key Lab Aerosp Power Syst, Nanjing 21006, Jiangsu, Peoples R China;

    Nanjing Univ Aeronaut & Astronaut, Jiangsu Prov Key Lab Aerosp Power Syst, Nanjing 21006, Jiangsu, Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Supersonic wind tunnel; Starting characteristics; Moving shock wave; Total pressure loss; Inlet model;

    机译：超音速风洞;启动特性;移动冲击波;总压力损失;进气口模型;

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