低温跨声速风洞设计中的真实气体效应研究  

Real-gas effects research associated with cryogenic transonic wind tunnel

作　　者：黄知龙 王宁[2] 史志伟[1] 廖达雄[2] HUANG Zhilong;WANG Ning;SHI Zhiwei;LIAO Daxiong(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautices,Nanjing 210016,China;Facility Design and Instrumentation Instiute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]南京航空航天大学航空学院,江苏南京210016 [2]中国空气动力研究与发展中心设备设计与测试技术研究所,四川绵阳621000

出　　处：《国防科技大学学报》2023年第1期110-116,共7页Journal of National University of Defense Technology

基　　金：空气动力学国家重点实验室基金资助项目(JBKY17040403)。

摘　　要：风洞以低温气体为介质运行时,气体会表现出热力和热值的不完全,风洞回路气体流动参数计算需要考虑低温真实气体效应。计算给出了氮气介质在温度100~323 K、压力100~450 kPa范围压缩性因子和比热比的变化规律,并通过将等熵膨胀系数引入一维完全气体流动方程,发展了低温跨声速风洞气流流动参数计算分析模型,获得了跨声速风洞高速运行时气流液化温度和压力的组合边界包络线。对比分析结果表明:在低温跨声速风洞的运行压力(115~450 kPa)和温度(110~323 K)范围内,基于等熵膨胀系数计算得到的气体流动状态参数的理论计算值与气体真实物理解的偏差小于1%,完全可满足低温跨声速风洞工程设计需求。The thermodynamic and calorific of the gas in wind tunnel will be imperfect when the wind tunnel operates under cryogenic temperature. In this case, the real gas effects should be considered for calculating flow parameters. The change laws of the compressibility factor and specific heart ratio for nitrogen gas under the ranges of pressures(100~450 kPa)and temperatures(100~323 K) were presented. By introducing the isentropic expansion coefficient into one-dimensional perfect gas flow equations, the computational analysis model for cryogenic wind tunnel flow parameters was developed, and the operating envelope of transonic wind tunnel considering the gas liquefaction temperature and pressure under high speed was obtained. The analysis results show that for the ranges of pressures(115~450 kPa) and temperatures(110~323 K) that cover the range of operation of transonic cryogenic wind tunnel, the maximum deviation of the various isentropic parameters from the ideal values is about 1% or less, and this deviation would be insignificant for the aerodynamic designing of the cryogenic transonic wind tunnel.

关 键 词：真实气体效应 低温风洞 工程设计 跨声速风洞 等熵流动 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]