超声速静风洞设计和流场校侧  

The Aerodynamic and Structural Design of Supersonic Quiet Wind Tunnel

作　　者：周勇为[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》2005年第6期5-8,92,共5页Journal of National University of Defense Technology

基　　金：国防预研基金资助项目(97J13.1.3KG0145)

摘　　要：论述了静风洞概念并设计和建立了一座小型静风洞SQWT-120.SQWT-120的设计马赫数为4.0,喷管出口直径为120mm,Re=0.46～1.78×107,运行时间为6～60s.测量结果表明,喷管出口马赫数为3.8,在x从160～438mm一段轴向距离内,ΔM/≯±1.2%.在P0＝0.4MPa,喷管出口6cm处,静压脉动值不超出0.1%,风洞工作时间15s,具备静风洞试验能力.A basic idea of a quiet wind tunnel is described. A supersonic quiet wind tunnel（SQWT- 120） is designed and built. SQWT- 120 designed Mach number is 4.0, the nozzle outlet diameter is 120mm, Re is 0.46 - 1.78× 10^7 and the operation duration is 6 - 60 seconds. The conclusions of calibrations demonstrate the actual flow Maeh number is 3,8, △M/M^-≯±1.2% between x = 160mm and x = 438mm. The unsteady pressure disturbances are not larger than 0.1% before x = 450mm, the operation time is 15s. The results show that the wind tunnel can be used to study the steady flow and unsteady flow.

关 键 词：超声速 静风洞 设计 校侧 

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]