TSP技术在转捩检测中的应用研究  

Application research of TSP technique in transition detection

作　　者：尚金奎[1] 王鹏[1] 陈柳生[2] 衷洪杰[1] 赵民[1] 

机构地区：[1]中航工业空气动力研究院,辽宁沈阳110034 [2]中国科学院化学研究所,北京100190

出　　处：《空气动力学学报》2015年第4期464-469,共6页Acta Aerodynamica Sinica

摘　　要：在研究型风洞中进行TSP转捩检测技术的应用研究,以NACA0012二元翼型为研究对象,获得了模型表面转捩位置。试验中应用了国内具有自主知识产权的TSP涂料,对模型进行了预加热,模型预加热的目的是提升TSP涂层的温度敏感度,并增大模型表面层流区与湍流区之间的温度差。模型表面粘贴了标记点,目的是将其作为图像对准的控制点,同时,模型前缘附近的标记点也可以作为人工固定转捩的粗糙元,起到强制气流转捩的目的。试验马赫数为0.4,迎角α为0°^-4°,试验结果清晰地显示了模型表面的层流区与湍流区及其随迎角的变化,表明所用的TSP涂料在本试验中具有良好的适用性,模型前缘附近标记点也起到了粗糙元的作用。A wind tunnel test which uses TSP transition detection technique is introduced. The NACA0012 model is uniformly covered with TSP developed by AVIC ARI and ICCAS, and the model is heated before wind tunnel running to increase the temperature difference between laminar flow area and turbulent flow area around the model surface. The marks are stuck to the TSP coat which will be used in the image processing, and some of them will be used as the transi- tion start-up roughness elements. The wind tunnel test condition is Mach 0.4 and angle of attack of 0°,-1°, -2°, -3 °, -4° respectively. The test results clearly show the difference between the lam- inar flow area and the turbulent flow area of the model surface, and the change along with the model angle of attack. It is shown that the TSP works well, and the marks near the model lead- ing edge cause the transition from laminar flow to turbulent one functionated as roughness ele- ments in this test.

关 键 词：TSP 转捩 NACA0012 温度测量 风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]