2.4m跨声速风洞流场性能调试研究

Investigation on flow-field debugging for 2.4m transonic wind tunnel

介绍了2.4m跨声速风洞性能调试研究结果,并作了简要分析。研究结果表明,该风洞流场品质全面达到国军标指标,部分达到当今世界先进水平。该研究首次在国内四壁均为斜孔壁的大型跨声速风洞中解决了优化开闭比、加速区分布形式以及特大驻室M数参考点位置确定等一系列技术问题,表明我国大型跨声速风洞流场性能调试研究取得新进展。

This paper presents the flow-field debugging results in 2.4 m Transonic Wind Tunnel. The debugging items include porosity options and accelerative area distribution arrangement, the effects of test section wall's diffused angle and blockage of model and testing total pressure on the flow-field uniformity, the referring point of Mach number options in ultra-large settling chamber, wave elimination characteristics of the walls, the thickness measurement of the boundary layer of the side walls and so on. The results indicate that the flow-field quality has met the requirements of the National and Military Standards and hit the designing targets. Furthermore, some has reached the world advanced standards. The thickness of the boundary layer of the side walls is thinner than that of FL-24 Transonic and Supersonic Wind Tunnel at all testing Mach numbers. This investigation, for the first time, resolves the technical difficulties such as porosity options and the accelerative area distribution arrangement in large-type transonic wind tunnel with 4 perforated walls with 60° inclined holes. This marks that the flow-field debugging techniques of large-type transonic wind tunnel in our country have stepped into a new stage.