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[Objective] Compressible Aerodynamics is a core course in the undergraduate curriculum for Aircraft Design and Engineering. The course focuses on aerodynamic phenomena and governing principles under high-speed flow conditions and serves as a critical foundation for the education and training of future aircraft designers. However, instruction in compressible aerodynamics currently suffers from a severe shortage of experimental components, which limits students' ability to connect theoretical concepts with physical flow behavior. To address this deficiency, this study develops an experimental teaching platform for compressible aerodynamics based on a newly constructed supersonic Ludwieg tube tunnel. By systematically integrating theoretical instruction with hands-on experimentation, the platform establishes a solid experimental foundation for cultivating high-level talent in Aircraft Design and Engineering. [Methods] Using Mach number measurement in a hypersonic wind tunnel as a representative example, this paper presents the fundamental operating principles of the Ludwieg tube and the theoretical basis and formula derivations for determining the incoming-flow Mach number using Pitot probes. A dedicated hypersonic wind tunnel experiment was designed to guide students through the measurement process, enabling them to develop a deeper understanding of normal shock wave theory and the correct application of isentropic relations in compressible aerodynamics through experimental design and practice. [Results] High-speed schlieren visualization techniques were employed to observe the formation and evolution of detached shock waves ahead of Pitot probes, thereby rendering otherwise invisible aerodynamic phenomena directly observable. This visualization intuitively demonstrates the complete process of flow establishment within a hypersonic wind tunnel and significantly enhances students' conceptual understanding of key topics in compressible aerodynamics. Using Pitot probes in combination with pressure sensors, total pressure measurements were obtained upstream and downstream of shock waves at different incoming flow Reynolds numbers. Based on the Pitot–Rayleigh relationship derived from normal shock theory, the free-stream Mach number distribution in the test section was calculated for each case. The experimental results indicate that increasing the incoming flow Reynolds number leads to a thinner boundary layer at the nozzle exit, an increased effective area ratio between the nozzle exit and throat, and consequently a higher Mach number in the wind tunnel test section. [Conclusions] The Ludwieg tube hypersonic wind tunnel experimental teaching platform has been successfully implemented in undergraduate education at our institution and has since been widely used in both undergraduate and graduate experimental teaching. By overcoming the inherent limitations of conventional hypersonic wind tunnels—namely, prohibitive construction costs, high operational expenses, and limited accessibility—this platform provides a practical model for experimental instruction in compressible aerodynamics and offers a viable approach for training students in hypersonic experimental aerodynamics in China.
[1]ANDERSON J D. Modern compressible flow:With historical perspective[M]. 2nd ed. New York:Mc Graw-Hill Book Company, 2003.
[2]LIEPMANN H W, ROSHKO A. Elements of gasdynamics[M].New York:Dover Publications, 2002.
[3]TSIEN H S. Similarity laws of hypersonic flows[J]. Journal of Mathematics and Physics, 1946, 25(1-4):247–251.
[4]ANDERSON J D. Fundamentals of aerodynamics[M]. New York:McGraw-Hill Book Co, 1984.
[5]韩忠华,宋文萍,宋科,等.“可压缩空气动力学”一流课程建设中的课程思政改革与实践[C]//第三届全国航空航天类课程思政教学改革论坛论文集,西安, 2022:143–147.HAN Z H, SONG W P, SONG K, et al. Reform and practice of curriculum ideology and politics in the construction of the first-class course“Compressible Aerodynamics”[C]//Proceedings of the 3rd National Forum on Ideological and Political Teaching Reform for Aerospace Courses, Xi’an 2022:143–147.(in Chinese)
[6]贾永霞,顾斌,徐胜金.风洞实验直播教学方法研究[J].实验技术与管理, 2018, 35(6):27–30.JIA Y X, GU B, XU S J. Research on live broadcast teaching method for wind tunnel experiment[J]. Experimental Technology and Management, 2018, 35(6):27–30.(in Chinese)
[7]张刃,杜文天,李庆利,等. 2.4 m连续式跨声速风洞气动设计与研究[J].空气动力学学报, 2023, 41(1):22–38.ZHANG R, DU W T, LI Q L, et al. Aerodynamic design of2.4 m continuous transonic wind tunnel[J]. Acta Aerodynamica Sinica, 2023, 41(1):22-38.(in Chinese)
[8]尤文佳,王慧杰,韩仁坤,等.高超声速风洞现代试验设计方法研究[J].实验流体力学. 2022. 36(3):20–32.YOU W J. WANG H J. HAN R K, et al. Using modern design of experiments method for hypersonic wind tunnel test[J]. Journal of Experiments in Fluid Mechanics, 2022, 36(3):20–32.(in Chinese)
[9]徐来武,熊波,阎成,等.新1.2 m高速风洞性能调试与优化研究[J/OL].实验流体力学, 1–10.(2025-07-11)[2025-07-18].https://link.cnki.net/urlid/11.5266.V.20250711.1006.002.XU L W, XIONG B, YAN C, et al. Research on performance adjustment and optimization of new 1.2 m high speed wind tunnel[J/OL]. Journal of Experiments in Fluid Mechanics, 1–10.(2025-07-11)[2025-07-18]. https://link.cnki.net/urlid/11.5266.V.20250711.1006.002.(in Chinese)
[10]SINGH S, YOERG E, HAYES G, et al. Design of a supersonic wind tunnel at Embry-Riddle Aeronautical University[C]//AIAA SciTech Forum and Exposition Applied Aerodynamics,Orlando, FL, USA, 2025, 1:11–21.
[11]江贤洋,李存标.高超声速边界层感受性研究综述[J].实验流体力学, 2017, 31(2):1–11.JIANG X Y, LI C B. Review of research on the receptivity of hypersonic boundary layer[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(2):1–11.(in Chinese)
[12]景喜双,张承阳,谢福宝,等.基于重点实验室的航空制造领域卓越工程师“三位一体”培养模式[J].实验技术与管理,2024, 41(5):237–242.JING X S, ZHANG C Y, XIE F B, et al. Trinity training model of outstanding engineers in the field of aviation manufacturingbased on the key laboratory[J]. Experimental Technology and Management,2024, 41(5):237–242.(in Chinese)
[13]荣臻.高超声速风洞虚拟仿真实验教学项目设计与实现[J].实验室研究与探索, 2022, 41(8):272–277.RONG Z. Design and Implementation of Hypersonic Wind Tunnel Virtual Simulation Experiment Teaching Project[J].Research and Exploration in Laboratory, 2022, 41(8):272–277.(in Chinese)
[14]陆小革,易仕和,周勇为,等.Φ300 mm高超声速静风洞的设计[C]//第九届全国实验流体力学学术会议论文集（下册）,杭州, 2013:155–161.LU X G, YI S H, ZHOU Y W, et al. The design ofΦ300 mm hypersonic quite wind tunnel[C]//Proceedings of the 9th National Academic Conference on Experimental Fluid Mechanics(VolumeⅡ), Hangzhou, 2013:155–161.(in Chinese)
[15]徐翔,程克明,王志坚,等.南航Φ0.5 m高超声速风洞流场校测[J].实验流体力学, 2009, 23(4):77–81.XU X, CHENG K M,WANG Z J, et al. Flow field calibration of NUAAΦ0.5 m hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2009, 23(4):77–81.(in Chinese)
[16]杨固,张霖,陈明福,等.北京大学四号风洞微型机实验过程控制及数据采集处理系统[J].实验技术与管理, 1984(1):48–57.YANG G, ZHANG L, CHEN M F, et al. Microcomputer experimental process control and data acquisition and processing system for No.4 wind tunnel of Peking University[J].Experimental Technology and Management, 1984,(1):48–57.(in Chinese)
[17]刘年凯.清华大学工程力学研究班学习及清华大学超声速风洞建设:章光华教授访谈录[J].中国科技史杂志, 2024,45(3):551–561.LIU N K. Studying in the research class of engineering mechanics and constructinga supersonic wind tunnel in Tsinghua University:An interview with Prof. Zhang Guanghua[J]. The Chinese Journal for the History of Science and Technology,2024, 45(3):551–561.(in Chinese)
[18]LUDWIEG H. Der Rohrwindkanal[J]. Zeitschrift für Flugwissenschaften, 1995, 3(7):206–216.
[19]KOPPENWALLNER G, MÜLLER-EIGNER R, FRIEHMELT H.HHK Hochschul-Hyperschall-Kanal:Ein‘Low-Cost’ Windkanal für Forschung und Ausbildung[J]. DGLR-Jahrbuch, 1993, 2:887–896.
[20]SCHRIJER F. Experimental investigation of re-entry aerodynamic phenomena[D]. Delft:Technische Universtiteit Delft, 2010.
[21]SCHRIJER F F, BANNINK W J. Description and flow assessment of the Delft hypersonic ludwieg tube[J]. Journal of Spacecraft and Rockets, 2010, 47(1):125–133.
[22]赵家权,司马学昊,黄冉冉,等.一种采用双弯管储气段布局的高超声速Ludwieg管设计[J].空气动力学学报, 2022,40(4):90–100.ZHAO J Q, SIMA X H, HUANG R R, et al. Design of a hypersonic Ludwieg tunnel with a double-bent storage tube[J].Acta Aerodynamica Sinica, 2022, 40(4):90-100.(in Chinese)
[23]LI Z, XIONG Y, YUAN X, et al. A variant design of hypersonic Ludwieg tube wind tunnel[J]. AIAA Journal, 2022, 60(7):3990–4005.
[24]RADESPIEL R, ESTORF M, HEITMANN D, et al. Hypersonic Ludwieg tube:Experimental methods of shock wave research[M]. Berlin Springer, 2016:433–458.
[25]朱海军,王倩,梅笑寒,等.基于高速纹影/阴影成像的流场测速技术研究进展[J].实验流体力学, 2022, 36(2):49–73.ZHU H J, WANG Q, MEI X H, et al. A review on flow field velocimetry based on high-speed schlieren/shadowgraph systems[J]. Journal of Experiments in Fluid Mechanics, 2022, 36(2):49–73.(in Chinese)
Basic Information:
DOI：10.16791/j.cnki.sjg.2026.02.019
China Classification Code:V211.7-4;G642.423
Citation Information:
[1]WU Jie,LI Chuangchuang,LI Zhiyuan ,et al.Experimental teaching of compressible aerodynamics based on a Ludwieg tube tunnel[J].Experimental Technology and Management,2026,43(02):162-170.DOI:10.16791/j.cnki.sjg.2026.02.019.
Fund Information:
国家自然科学基金面上项目(12472334)
2025-07-28
2025
2025-09-02
2025
2025-09-02
1
2026-02-27
2026-02-27
2026-02-27