Φ120高超声速风洞流场校测  

Φ120 Hypersonic Wind Tunnel Flow Field Calibration

作　　者：荣臻[1] 胡文杰 邱云龙 张玉剑 王亦庄 江中正 陈伟芳[1] RONG Zhen;HU Wenjie;QIU Yunlong;ZHANG Yujian;WANG Yizhuang;JIANG Zhongzheng;CHEN Weifang(School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,Zhejiang,China)

机构地区：[1]浙江大学航空航天学院,浙江杭州310027

出　　处：《空天防御》2022年第3期58-64,共7页Air & Space Defense

基　　金：国家自然科学基金青年基金项目(No.12002306);国家自然科学基金联合基金项目(No.U20B2007);中国电波传播研究所稳定支持科研经费资助项目(No.A132004W21)。

摘　　要：介绍了浙江大学Φ120高超声速风洞的设计性能参数、流场校测结果以及标模测力结果。Φ120高超声速风洞采用“前吹后吸”的暂冲式直连式布局,喷管出口直径为120 mm,设计运行马赫数为5.0、6.0和7.0,来流总压0.2~2.0 MPa,来流总温400~700 K,运行时间不小于10 s。流场校测结果显示5.0/6.0/7.0喷管的均匀区直径超过90 mm,均匀区平均马赫数分别为5.07、6.05和6.94,均方根偏差分别为0.018、0.015和0.023,均匀区轴向马赫数梯度分别为0.021、0.016和0.031,上述关键参数全部达到GJB1179A-2012合格指标,部分参数达到GJB1179A-2012先进指标。AGARD HB-2标模在Φ120高超声速风洞中的气动力测量结果与自研GRAND程序数值计算结果以及GJB4399-2002中的参考值吻合得较好。综上所述,Φ120高超声速风洞参数范围较宽,可用于高超声速空气动力学教学试验和高超声速复杂流动机理、流动控制降热减阻机制等前沿科学问题的研究。This paper introduces the design performance parameters,flow field calibration results and standard model force measurements ofΦ120 hypersonic wind tunnel of Zhejiang University.This wind tunnel adopts conventional"blow-suck"layout.The diameter of the nozzle outlet is 120 mm;the design operation Mach number is 5.0,6.0 and 7.0;the total pressure of the incoming flow is 0.2~2.0 MPa;the total temperature of the incoming flow is 400~700 K;and the running time is not less than 10 seconds.The flow field calibration results show that the uniform region diameters of the 5.0/6.0/7.0 nozzles are more than 90mm;the average Mach numbers of the uniform region are 5.07,6.05 and 6.94;the rms deviations are 0.018,0.015 and 0.023;and the axial Mach gradients of the uniform region are 0.021,0.016 and 0.031 respectively.All the above key parameters reach the GJB1179A-2012 qualified indices,and some parameters reach the GJB1179A-2012 advanced indices.The aerodynamic force measurement results of the AGARD HB-2 standard model in theΦ120 hypersonic wind tunnel are consistent with the simulation results of in-house code GRAND and the reference experimental results in GJB4399-2002.In summary,Φ120 hypersonic wind tunnel has a wide range of parameters,which is applicable for hypersonic aerodynamic teaching experiments and advanced scientific research subjects such as hypersonic complex flow mechanism and flow control for heat and drag reduction.

关 键 词：高超声速 风洞 流场校测 气动力 

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]