大型亚声速风洞试验段设计的新概念

New Concept Open Jet Test Section for Large Subsonic Wind Tunnel

下载PDF

导出

摘要用一个亚声速引导性风洞的研究数据揭示了常规开口试验段设计中存在的问题及一些解决方法;介绍了国外亚声速风洞开口试验段设计的新概念,使风洞试验段允许的模型堵塞度从10%提高到20%,大幅度降低风洞的建造和运营成本,为国内未来大型亚声速风洞建设的创新设计提供参考。

作者战培国

机构地区中国空气动力研究与发展中心

出处《航空科学技术》 2012年第4期69-72,共4页 Aeronautical Science & Technology

关键词亚声速风洞风洞设计试验段 subsonic wind tunnel, wind tunnel design test section

参考文献9

1Lacey J J. Concept for reducing the cost of subsonic wind tunnels[R]. AIAA 2004-6828.
2Jacobs E. Investigation of air flow in open throat wind tunnels[R]. NACA Report 322, 1929.
3Manuel G. Effect of collector configuration on test section turbulence levels in an open-jet wind tunnel[R]. NASA TM-4333,July 1992.
4Schulz- Influence of test collector area on Hausmann F, Vagt J. : section length and measurements in 3/4 open jet automotive wind tunnels[R] SAE 880251,March 1988.
5Arnette. On low-frequency pressure pulsations and static pressure distribution in open jet tunnels[R]. SAE 1999 automotive wind- 01 -0813.
6John J L. Concept for reducing the cost of subsonic wind tunnels[R]. AIAA 2004-6828.
7Rennie M. Effect of jet length on pressure fluctuations in 3/4 open-jet wind tunnels[C]. Motor Industry Research Association Vehicle Aerodynamics 2000 Symposium, October 2000.
8Walter J. The DaimlerChrysler full-scale aeroacoustic wind tunnel [R]. SAE 2003-01 0426, March 2003.
9Rennie M. Suppression of open- jet pressure fluctuations in the Hyundai aeroacoustic wind runnel[R]. SAE 2004- 01-0803, March 2004.

航空科学技术

2012年第4期

内容加载中请稍等...