摘要
南航NHWΦ0.5m高超声速风洞试验马赫数为5、6、7和8,建成后对风洞流场进行了速度场校测和A-GARD-HB-2标模测力试验。介绍了M5和M8喷管速度场校测和标模试验。结果表明:风洞均匀区范围可达336mm;截面内最大马赫数偏差,M5喷管流场|ΔMaj|max/Maj=0.006,M8喷管流场|ΔMaj|max/Maj=0.007;截面标准差,M5喷管流场σMaj/|ΔMaj|max=0.378,M8喷管流场σMaj/|ΔMaj|max=0.484。上述各项条件均满足GJB4399-2002对风洞速度场的要求。经过对比,NHW风洞的标模测力结果与国内风洞试验数据吻合较好且全部在AGARD-HB-2数据带内,这证明了该风洞试验数据的准确性。流场校测和标模试验的结果证明了该风洞满足设计指标。
Here presented in this paper are the calibration of flow field and force experiments of standard model AGARD-HB-2 carried out in NUAA Ф0.5m hypersonic wind tunnel at Maeh number of 5,6,7 and 8. Calibration tests and standard model tests for nozzles at M5 and M8 are given in this paper. Diameters of the uniform field reach 336mm; maximum deviation of Mach number ｜ △Maj｜ max is 0.006 at M5 and 0.007 at M8 respectively; standard deviation of Mach number σMaj is 0. 378 at M5 and 0.484 at MS. All the parameters mentioned above meet the requirements of GJB4399-2002. Comparison of AGARD-HB-2 model force measurement data with domestic wind tunnels validated the accuracy of test data obtained by this facility. The flow field calibration and standard model tests indicate that this wind tunnel has met the design requirements.
作者
徐翔
程克明
王志坚
徐筠
Xu, Xiang[1]; Cheng, Ke-Ming[2]; Wang, Zhi-Jian[3]; Xu, Yun[3]
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2009年第4期77-81,共5页
Journal of Experiments in Fluid Mechanics
基金
The authors acknowledge the support from College of Aerospace Engineering of Nanjing University of Aeronauticsand Astronautics(NUAA),and Hypervelocity Aerodynamic Institute of China Aerodynamics Research ＆ Development Center(CARDC).
关键词
高超声速风洞
速度场校测
标模
测力试验
hypersonic wind tunnel
calibration of velocity field
standard model
force test
