M6高超声速静风洞的气动设计和结构研究  

The Aerodynamic and Structural Research of Mach6 Hypersonic Quiet Wind Tunnel

作　　者：周勇为[1] 易仕和[1] 陈植[1] 陆小革[1] 葛勇[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2011年第3期14-17,43,共5页Journal of National University of Defense Technology

基　　金：国家省部资助项目

摘　　要：论述了发展高超声速静风洞设备与技术的重要性，对静风洞的基本特点进行了简要讨论。根据国内外发展静风洞的经验和成果，针对开展静风洞的实验技术及边界层稳定性问题研究的背景，提出一座M6高超声速静风洞（M6HQWT）的气动和结构设计，重点讨论了阀门管路、稳定段和喷管抽吸装置的设计特点。M6HQWT的设计马赫数为6．0，喷管出口直径120mm，总压l一5MPa，总温约500K，运行时间20～30s。M6HQWT是国内第一座高超声速静风洞，具备实验教学和基础科学研究的能力。First, the importance of developing hypersonic quiet tunnel facility and techniques was pointed out, and the basic characteristics of quiet tunnel were briefly discussed. Second, according to foreign and domestic experience and research results of developing quiet tunnel, the project about aerodynamic and structmal research of mach 6 Hypersonic Quiet Wind Tunnel was presented. Furthermore, the design details of valves, settling chamber and slot exhaust of nozzle were proposed. Finally, M6HQWT design Mach number is 6.0, nozzle outlet diameter 120mm, To 500K, P0 1-5MPa and operation duration 20-30s. M6HQWT is the first hypersonic quiet wind tunnel in China, and can be used for experimental teaching and basic scientific research.

关 键 词：高超声速 静风洞 层流喷管 边界层 噪声 

分 类 号：V411.7[航空宇航科学与技术—航空宇航推进理论与工程]