摘要
介绍在JF-10氢氧爆轰驱动高焓激波风洞中开展再入流场红外辐射测量的实验技术.风洞试验状态的驻室总压为19.6MPa,驻室总温为7920K.实验以球头钝锥体为试验模型,测量其近尾流红外辐射能量通量的横向分布.测量采用插入式锑化铟多元红外成像系统,波段范围为2.27～6.0μm.试验数据呈现明显的规律性.试验结果表明:利用这一测量技术能够提供高焓条件下有较高空间分辨率的、较为准确的红外实验数据.
This paper mainly introduces the experimental technique of infrared radiation from 2.27 to 6.0μm in wake of blunt cone acting as reentry model in JF-10 oxygen hydrogen detonation driven shock tunnel. The total pressure Po is 19.6MPa. The total temperature To is 7920K. The result shows obvious regularity, proving that, this technique can provide experimental infrared radiation data which is correct enough and have space distinguishing power.
出处
《实验流体力学》
CAS
CSCD
北大核心
2005年第4期69-73,共5页
Journal of Experiments in Fluid Mechanics
基金
国家自然科学基金资助项目
项目批准号:10472125
关键词
氢氧爆轰驱动激波风洞
再入流场
红外辐射
钝体
尾流
oxygen hydrogen detonation driven shock tunnel
reentry flow
infrared radiation
blunt cone
wake
