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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。
The key technologies and solutions for the experimental study of PSP in hypersonic wind tunnel are put forward. The self-designed PSP calibration system and test system were used to test the applicability of the pressure-sensitive coating codenamed “EC-PSP” under hypersonic conditions, the function of image processing software and the feasibility of data processing methods under the influence of high temperature conditions. Taking the compression corner model as an example, a hypersonic PSP-based validation wind tunnel experiment with a Mach number of 5 was carried out, supplemented by infrared temperature measurement to obtain a continuous temperature distribution on the model surface. The experimental results show that the PSP test technique in the hypersonic wind tunnel clearly captures the surface flow characteristics of the compression corner model based on the pressure variation and realizes the measurement of the continuous pressure distribution.