Φ200高超声速风洞调试和流场校测  

The Test and Calibration of Φ200 Hypersonic Wind Tunnel

作　　者：周勇为[1] 易仕和[1] 程忠宇[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2009年第6期57-61,共5页Journal of National University of Defense Technology

基　　金：国家部委资助项目

摘　　要：介绍了新近建成的马赫数为2.5-7.0的Φ200mm高超声速风洞（Φ200 Hypersonic Wind Tunnel,HWT-200）调试情况及空风洞流场校测结果。调试校测结果表明,风洞的总温、总压、运行时间等参数完全达到了设计要求,顺利实现了宽马赫数范围下的超声速/高超声速运行;本风洞有较大的实验段流场均匀区,各流场的马赫数均方根偏差全部达到GJB（1179-91）的合格指标,一部分达到了先进指标。风洞运行时间不少于20s,是一座参数范围较宽、运行成本较低、维护方便、可用于空气动力学教学试验和基础性科学研究的设备。The newly finished Ф200 hypersonic wind tunnel（Mach numbers 2.5 to 7） has been tested and calibrated. The results of calibration indicating total temperature, total pressure, operating time of HWT-200 have accorded with the purpose of design. HWT-200 can run within large Mach number span at supersonic/hypersonic flow. The rms of Mach numbers （ σM ） at all test sections Mach numbers from 2.5 to 7.0 reaches the requirement of GJB1179-91. A large, uniform region of flow was documented. Operational time of HWT- 200 is no less than 20s. So, HWT-200 is a facility which can be used for teaching of aerodynamic experiments and elementary scientific researches.

关 键 词：高超声速 风洞 风洞调试 流场校测 

分 类 号：V411.7[航空宇航科学与技术—航空宇航推进理论与工程]