| 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 |
| |
| 引用本文： | 陈星,文帅,潘俊杰,姚大鹏,毕志献. 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[J]. 气体物理, 2017, 2(2): 54-63. DOI: 10.19527/j.cnki.2096-1642.2017.02.007 |
| |
| 作者姓名： | 陈星 文帅 潘俊杰 姚大鹏 毕志献 |
| |
| 作者单位： | 中国航天空气动力技术研究院，北京 100074 |
| |
| 基金项目： | 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.
|
| 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 |
| 收稿时间： | 2016-09-11 |
Delta Wing Model Skin Friction Measurement Test and Data Confirming in Hypersonic Wind Tunnel |
| |
| Affiliation: | China Academy of Aerospace Aerodynamics, Beijing 100074, China |
| |
| Abstract: | A creative application of global skin friction measurement based on shear-sensitive liquid crystal coatings(SSLCCs) 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 experiments prove the SSLCCs method practicable, and it valuably solves the hard technological problem of skin friction measurement in hypersonic flow condition. |
| |
| Keywords: | |
| 本文献已被 CNKI 等数据库收录！ |
| 点击此处可从《气体物理》浏览原始摘要信息 |
|
点击此处可从《气体物理》下载免费的PDF全文 |
