大型高超声速风洞真空模式调试及流场性能校测  

Vacuum mode debugging and flow field performance calibration of large-scale hypersonic wind tunnel

作　　者：马利川[1] 石运军 黄炳修[1] 孙勇堂[1] 晏硕 MA Lichuan;SHI Yunjun;HUANG Bingxiu;SUN Yongtang;YAN Shuo(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2022年第1期96-102,共7页Journal of Experiments in Fluid Mechanics

摘　　要：未来先进飞行器飞行高度不断增大,对风洞试验模拟能力的要求不断提高,需要高超声速风洞具备更低真空的运行能力,常规多级引射系统已不能完全满足要求。为提高风洞试验高度模拟范围,中国航天空气动力技术研究院(CAAA)在新建Φ1.2 m高超声速风洞基础上设计专用真空排气支路,实现了风洞压力真空模式运行。风洞系统调试及校测结果表明:经能力提升改造后,风洞各分系统工作正常且均达到性能设计指标,实现了马赫数5~8、高度40 km以上的高空低雷诺数高超声速试验条件模拟能力,试验段均匀区流场指标满足GJB 4399-2002高超声速风洞气动力试验的相关要求,为高空条件下飞行器气动特性及复杂高超声速流动问题的研究提供了试验平台。With the continuous increase of the flight altitude of advanced aircraft in the future,the requirements for wind tunnel test simulation ability are constantly increasing, such as the lower vacuum running ability. The conventional multistage ejection system can no longer fully meet the operation requirements. In order to improve the height simulation range of the wind tunnel test, CAAA designed a vacuum exhaust branch based on the original equipment of its newly built Ф1.2 m hypersonic wind tunnel to realize the pressure vacuum mode operation of the wind tunnel. The wind tunnel system debugging and testing results show that after the wind tunnel capacity is improved, each subsystem works normally and the system performance reaches the design target, and the hypersonic flow field condition at the altitude above 40 km with Mach number 5– 8 is realized. The flow field index in the uniform area of the test section meets the relevant requirements of the aerodynamic test of the National military standard GJB 4399-2002.It provides a test platform for the study of aerodynamic characteristics of aircraft and complex hypersonic flow at high altitude.

关 键 词：高超声速风洞 低雷诺数 压力真空 流场性能 

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]