高焓风洞中钝体近尾流红外辐射测试技术  

Experimental technique on infrared radiation in wake of blunt cone in high-enthalpy tunnel

作　　者：杭建[1] 林贞彬[1] 郭大华[1] 林建民[1] 曾明[1] 黄德[1] 葛学真[1] 

机构地区：[1]中国科学院力学研究所高温气体动力学实验室,北京100080

出　　处：《实验流体力学》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

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.

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 

分 类 号：V211.751[航空宇航科学与技术—航空宇航推进理论与工程]