Design and preliminary freestream calibration of HUST <i>Φ </i>0.5 m Mach 6 Ludwieg tube wind tunnel

HUANG Ranran; ZHANG Chengjian; LI Chuangchuang; XU Binghui; XU Duolong; YUAN Xianxu; WU Jie

doi:10.7638/kqdlxxb-2022.0146

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Design and preliminary freestream calibration of HUST Φ 0.5 m Mach 6 Ludwieg tube wind tunnel

更新时间：2026-05-28

- Design and preliminary freestream calibration of HUST Φ 0.5 m Mach 6 Ludwieg tube wind tunnel
- Vol. 41, Issue 1, Pages: 39-48, 85(2023)
- 作者机构：
  
  1. 华中科技大学航空航天学院,武汉,430074
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0146
  CLC： V211.751
- Published：2023
- 稿件说明：
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黄冉冉, 张成键, 李创创, 等. 华中科技大学Φ 0.5 m马赫6 Ludwieg管风洞设计与流场初步校测[J]. 空气动力学学报, 2023, 41(1): 39−48, 85.

HUANG Ranran, ZHANG Chengjian, LI Chuangchuang, et al. Design and preliminary freestream calibration of HUST Φ 0.5 m Mach 6 Ludwieg tube wind tunnel[J]. 2023, 41(1): 39-48, 85. DOI: 10.7638/kqdlxxb-2022.0146.
黄冉冉, 张成键, 李创创, 等. 华中科技大学Φ 0.5 m马赫6 Ludwieg管风洞设计与流场初步校测[J]. 空气动力学学报, 2023, 41(1): 39−48, 85. DOI： 10.7638/kqdlxxb-2022.0146

HUANG Ranran, ZHANG Chengjian, LI Chuangchuang, et al. Design and preliminary freestream calibration of HUST Φ 0.5 m Mach 6 Ludwieg tube wind tunnel[J]. 2023, 41(1): 39-48, 85. DOI: 10.7638/kqdlxxb-2022.0146. DOI：

摘要

高超声速风洞是研究高超声速空气动力学关键问题的重要手段，但是常规高超声速风洞建设和运行成本偏高，不利于深入开展高超声速飞行器部分空气动力学基础问题研究。本文以低成本研究型高超声速风洞设计为目标，基于Ludwieg管设计原理，开展了

0.5 m口径马赫数6高超声速Ludwieg管的气动设计。首先采用数值手段对储气段、快开阀以及Laval喷管设计进行了分析，重点关注了采用弯曲储气段的Ludwieg管风洞非定常启动过程，之后使用皮托耙和皮托管等对风洞实验段的自由来流进行了初步校测。结果表明，采用快开阀主控的Ludwieg管高超声速风洞可以获得良好的流动品质，弯曲储气段虽然会影响膨胀波系的传播强度，但对其传播速度以及风洞的流场品质影响不大；风洞初步校测的数据显示，该风洞的来流马赫数分布品质优良，且来流压力脉动幅值低于德国与美国同类管风洞。该研究为设计低成本、大口径、研究型高超声速风洞提供了参考，可服务于高超声速空气动力学关键气动问题的实验研究。

Abstract

Hypersonic wind tunnels are essential in the fundamental research of hypersonic aerodynamics. However

the low operating efficiency

low flow-field quality

and high construction and operating costs of conventional hypersonic wind tunnels make delicate experimental investigations difficult. This paper aims to design a low-cost and large-diameter research-oriented hypersonic wind tunnel based on a

0.5 m Mach 6 Ludwieg tube. The design of the storage tube

fast-opening valve

and Laval nozzle is analyzed using numerical s

imulations

particularly emphasizing the unsteady starting process of the Ludwieg tube tunnel with a bent storage tube. Preliminary freestream calibration of the Ludwieg tube is also conducted. Results show that the hypersonic Ludwieg wind tunnel controlled by the fast-opening valve can obtain high flow quality in the test section. The bent storage tube slightly affects the propagation intensity of the expansion waves locally. However

it does not affect the propagation speed of expansion waves within the storage tube and the freestream quality in the test section. The Mach number distribution in the test section is reasonably excellent. The Pitot probe results show that the intensity of freestream pressure disturbances is lower than in similar facilities in Germany and UAS. The wind tunnel

therefore

shows promising potential in experimental studies of hypersonic aerodynamics. Hopefully

this study will shed light on constructing a low-cost

research-oriented hypersonic wind tunnel.

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references

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Design and preliminary freestream calibration of HUST Φ 0.5 m Mach 6 Ludwieg tube wind tunnel

DOI：10.7638/kqdlxxb-2022.0146

摘要

Abstract

关键词

Keywords

references