高超声速低密度风洞红外热图技术初步研究  

Preliminary research of infrared thermographic technique in hypersonic low density wind tunnel

作　　者：李明[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《流体力学实验与测量》2003年第4期51-55,共5页Experiments and Measurements in Fluid Mechanics

基　　金：国家863资助项目

摘　　要：为了对红外测热与热电偶测热进行比较研究,在马赫数M∞=12,驻点温度T0=650K,驻点压力P0=1630kPa的高超声速稀薄气流中,对一平板斜坡薄壁模型进行了试验,试验结果表明这二者所获得的模型表面热流率符合得较好。与此同时,对模型表面发射率的测量、模型物面坐标与热图象素坐标的对应关系也进行了初步探讨,重点提出了在大极角情况下对发射率进行修正的方法,即根据模型表面不同位置的法线,调整红外热像仪镜头轴线,使被测量区域的极角尽可能小,以保证发射率在此范围内为常数。In order to compare heat transfer rates measured by infrared thermographic technique with these measured by thermocouple, experiments on the thin flat plate model with a ramp were carried out in hypersonic rarefield flow with nominal test conditions of Mach number 12, stagnation temperature 650K, stagnation pressure 1630kPa.Experimental results showed that the infrared data agreed with the thermocouple data. Meanwhile, the measurement of a model surface emittance as well as the relation between the coordinate on the model surface and the corresponding coordinate in infrared thermography was preliminarily discussed. The method,by means of which the axis of IR lens in infrared camera can be adjusted to make the optical incident angle as small as possible with respect to the different normal of model surface, was mainly presented, which was used to correct the model surface directional emittance in large optical-incident-angle conditions and keep emittance of model surface investigated region constant.

关 键 词：表面发射率 红外热图技术 高超声速低密度风洞实验 温度测量 红外热像仪 模型试验 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程] TN219[电子电信—物理电子学]