三角翼标模摩擦阻力测量的高超声速风洞实验与数据确认  

Delta Wing Model Skin Friction Measurement Test and Data Confirming in Hypersonic Wind Tunnel

作　　者：陈星[1] 文帅[1] 潘俊杰[1] 姚大鹏[1] 毕志献[1] CHEN Xing WEN Shuai PAN Jun- jie YAO Da- peng BI Zhi-xian(China Academy of Aerospace Aerodynamics , Beijing 100074, China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《气体物理》2017年第2期54-63,共10页Physics of Gases

基　　金：国家自然科学基金(11272301)

摘　　要：描述了剪切敏感液晶涂层(shear-sensitive liquid crystal coatings,SSLCCs)在高超声速风洞中针对三角翼标模进行表面摩擦阻力(简称摩阻)测量的应用情况.建立了基于剪切敏感液晶涂层光学测量系统,在中国航天空气动力技术研究院FD-07风洞中进行了三角翼摩阻测量实验,给出了三角翼表面摩阻分布数据,表明流场结构的复杂.实验结果证明了此方法进行高超声速摩阻测量的可行性,有效解决了在高超声速流场条件下表面摩阻预测的难题,具有重要的应用价值.A creative application of global skin friction measurement based on shear-sensitive liquid crystal coatings（SSL- CCs） for delta wing in hypersonic wind tunnel was described in this paper. A SSLCCs optical measurement system was built and some experiments were performed in FD-07 hypersonic wind tunnel of China Academy of Aerospace Aerodynamics （CAAA）. Global skin friction distributions of delta wing which show complicated flow structures were discussed. The exper-iments prove the SSLCCs method practicable, and it valuably solves the hard technological problem of skin friction measure-ment in hypersonic flow condition.

关 键 词：剪切敏感液晶涂层 剪切应力测量 平板三角翼 高超声速流场 

分 类 号：O354[理学—流体力学]