高超声速风洞压敏漆试验技术  

Pressure sensitive paint test technique in hypersonic wind tunnel

作　　者：林敬周[1] 解福田[1] 钟俊[1] 陈磊[1] 陈柳生[2] 

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [2]中国科学院化学研究所,北京100190

出　　处：《航空学报》2017年第7期187-195,共9页Acta Aeronautica et Astronautica Sinica

摘　　要：提出了适用于高超声速风洞开展压敏漆(PSP)试验研究的关键技术及解决办法。采用自主设计的PSP校准系统及测试系统,考核了代号为EC-PSP的压力敏感涂料在高超声速条件下的适用性、图像处理软件功能以及高温条件影响下数据处理方法的可行性。以压缩拐角模型为例开展了马赫数为5的高超声速PSP技术验证性风洞试验研究,辅以红外测温方法获得模型表面连续温度分布。试验结果表明在高超声速风洞开展的PSP试验技术研究清晰地捕获了基于压力变化的压缩拐角模型表面流动特征,实现了连续压力分布的测量。Some key technological problems and their solutions for pressure sensitive paint（PSP）testing in the hypersonic wind tunnel are discussed.The self-designed PSP calibration and measurement systems are used to examine the performances of EC-PSP,including applicability of the material in the hypersonic flow condition,function of image processing software,and feasibility of data processing method at high temperature.Based on the compression corner flow,hypersonic wind tunnel test at Mach number 5 are carried out to validate the PSP testing technique,and auxiliary means of infrared temperature-measuring is employed to acquire the temperature distribution on the model surface.The results show that based on the changes of the pressure on the surface of the compression corner model,the flow characteristics can be obtained with high-order accuracy,and continuous pressure distributions can be consequently obtained.

关 键 词：高超声速 风洞 压敏漆(PSP) 压缩拐角 图像处理 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]