| 引用本文: | 周勇为.超声速静风洞设计和流场校侧.[J].国防科技大学学报,2005,27(6):5-8 ,92.[点击复制] |
| ZHOU Yongwei.The Aerodynamic and Structural Design of Supersonic Quiet Wind Tunnel[J].Journal of National University of Defense Technology,2005,27(6):5-8 ,92[点击复制] |
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| 超声速静风洞设计和流场校侧 |
| 周勇为 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 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/M≯±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。 |
| 关键词: 超声速 静风洞 设计 校侧 |
| DOI： |
| 投稿日期：2005-07-01 |
| 基金项目:国防预研基金资助项目(97J13.1.3KG0145) |
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| The Aerodynamic and Structural Design of Supersonic Quiet Wind Tunnel |
| ZHOU Yongwei |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology，Changsha 410073，China)
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| Abstract: |
| 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 0.46～1.78×107and the operation duration is 6-60 seconds. The conclusions of calibrations demonstrate the actual flow Mach number is 3.8, ΔM/M is ≯±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. |
| Keywords: supersonic quiet tunnel design calibrations |
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