| 温敏漆技术及其在边界层转捩测量中的应用 |
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| 引用本文： | 张扣立,常雨,孔荣宗,周嘉穗,江涛,贾国鹏,刘祥.温敏漆技术及其在边界层转捩测量中的应用[J].宇航学报,2013,34(6):860-865. |
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| 作者姓名： | 张扣立 常雨 孔荣宗 周嘉穗 江涛 贾国鹏 刘祥 |
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| 作者单位： | 1.中国空气动力研究与发展中心空气动力学国家重点实验室，绵阳 621000；
2.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 |
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| 基金项目： | 空气动力学国家重点实验室研究基金资助（JBKY09050401） |
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| 摘 要： |
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| 关 键 词： | 边界层转捩 高超声速 温敏漆 激波风洞 热流 |
| 收稿时间： | 2012-07-13 |
Temperature Sensitive Paint Technique and Its Application in Measurement of Boundary Layer Transition |
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| ZHANG Kou li,CHANG Yu,KONG Rong zong,ZHOU Jia sui,JIANG Tao,JIA Guo peng,LIU Xiang.Temperature Sensitive Paint Technique and Its Application in Measurement of Boundary Layer Transition[J].Journal of Astronautics,2013,34(6):860-865. |
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| Authors: | ZHANG Kou li CHANG Yu KONG Rong zong ZHOU Jia sui JIANG Tao JIA Guo peng LIU Xiang |
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| Affiliation: | 1.State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2.Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China |
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| Abstract: | A temperature sensitive paint (TSP) technique is developed for the request of boundary layer transition measurement, and a test of hypersonic boundary layer measurement of a flat plate is done in CARDC 0.6m shock tunnel. By use of the TSP technique, the measurement of the hypersonic boundary layer transition of slab has been done in the shock tunnel. The test nominal Mach numbers are 8 and 10, the unit Reynolds numbers are 2.45×10 7/m and 4.48× 10 6/m respectively, and the yaw angle is 20°. The data of heat transfer and transition position obtained by the TSP and measurement results of the thin film heat transfer sensor match well. The results illustrate that the TSP technique has the ability to measure the hypersonic boundary layer transition of simple model qualitatively and quantitatively in shock tunnel. |
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| Keywords: | Boundary layer transition Hypersonic Temperature sensitive paint Shock tunnel Heat transfer |
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