实验技术与管理2026，Vol.43Issue(2)：162-170,9.DOI:10.16791/j.cnki.sjg.2026.02.019
基于Ludwieg管风洞的可压缩空气动力学实验教学研究
Experimental teaching of compressible aerodynamics based on a Ludwieg tube tunnel
摘要
Abstract
[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.关键词
可压缩空气动力学/Ludwieg管/实验教学改革/激波/纹影Key words
compressible aerodynamics/Ludwieg tube/experimental teaching reform/shock wave/schlieren分类
航空航天引用本文复制引用
吴杰,李创创,李志远,余颖,李昕,刘红军..基于Ludwieg管风洞的可压缩空气动力学实验教学研究[J].实验技术与管理,2026,43(2):162-170,9.基金项目
国家自然科学基金面上项目(12472334) （12472334）
