高超声速静风洞特点和发展概述  

Summarization of the Characteristics and Development of Hypersonic Quiet Wind Tunnel

作　　者：周勇为[1] 易仕和[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：《实验力学》2010年第2期167-172,共6页Journal of Experimental Mechanics

基　　金："985"资助项目

摘　　要：普通的高超声速风洞来流噪声和脉动要比实际飞行高一到两个数量级,要在风洞中进行高超声速转捩机理现象的研究,发展高超声速静风洞是十分必要的。为此,首先介绍了静风洞的基本概念,讨论了静风洞的几个关键技术和层流喷管的设计方法,并对静风洞的噪声特性和诊断手段进行了简单的分析。同时论述了国际上高超声速静风洞的发展现状、基本过程和发展水平,介绍了NASA几个代表性的高超声速静风洞实例。最后,整理了国外发展静风洞的经验和成果,对建设我国高超声速静风洞具有参考和借鉴价值。Conventional hypersonic wind tunnel suffers from high noises and fluctuations of incoming flow, which are typically one to two orders of magnitude higher than the practical fight levels. Quiet- flow hypersonic wind tunnel is very essential to develop in order to seek phenomenon of hypersonic transition in t key points of and diagnosis unnel. Thus, f technology and way are analyz irst of all, basic concept of quiet wind t design method about laminar nozzle are ed in this paper. At the same time, the unnel is recommended, several discussed, noise characteristic , basic developing process and present situation of overseas hypersonic quiet tunnel are discussed. In addition, several typical supersonic and hypersonic quiet wind tunnels of NASA are reviewed. In conclusion, it is very valuable and useful for developing Chinese own quiet-flow hypersonic wind tunnel based on the overseas experience and results.

关 键 词：高超声速 静风洞 低噪声 稳定段 层流喷管 

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]