超声速静风洞的气动设计  

The aerodynamic design of supersonic quiet wind tunnel

作　　者：周勇为[1] 常熹钰[1] 易仕和[1] 张艳[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：《流体力学实验与测量》2002年第1期61-66,共6页Experiments and Measurements in Fluid Mechanics

基　　金：国防预研基金资助项目 (97J1 3 1 3KG0 1 4 5)

摘　　要：论述国际上关于超声速静风洞发展的基本过程、发展水平和我国发展这一风洞实验设备与技术的必要性 ,对静风洞的基本概念、层流喷管的设计方法等有关环节进行了简单的论述与讨论。根据国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 ,提出一座静风洞 (SQWT - 1 2 0 )的气动设计 ,SQWT - 1 2 0的设计马赫数为4.0 ,喷管出口直径 1 2 0mm ,Re/m =0 .46～ 1 .78×1 0 7,运行时间 6～60s。The writer describes a basic development process of supersonic quiet tunnel in the world, including developing level and necessity of developing quiet tunnel facility and techniques of our country. Technologically relevant contents of quiet tunnel, such as basic conception of quiet tunnel and design method of laminarized nozzle, is simply discussed. Finally, according to foreign basic experience and research results of developing quiet tunnel, aiming at the background of developing the experimental technology of quiet wind tunnel and stability of boundary, the aerodynamic design of a supersonic quiet wind tunnel(SQWT-120) is presented. SQWT-120 design Mach numbers is 4.0, nozzle outlet diameter 120mm, Re /m 0.46～1.78×10 7 and operation duration 6～60 second.

关 键 词：超声速静风洞 气动设计 层流喷管 稳定性 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]