空气动力学学报2016，Vol.34Issue(6)：738-743,6.DOI:10.7638/kqdlxxb-2015.0151
CARDC 激波风洞 TSP 技术研究进展
Development of TSP technique in shock tunnel of CARDC
张扣立 1周嘉穗 1孔荣宗 1马晓伟 1江涛1
作者信息
- 1. 中国空气动力研究与发展中心 超高速空气动力研究所，四川 绵阳 621000
- 折叠
摘要
Abstract
Recent research progress of the TSP (Temperature Sensitive Paint)technique in China Aerodynamics Research and Development Center(CARDC)is summarized in the respects of fundamental principles,development of critical technology and its applications.A series of critical techniques have been developed including the dynamic temperature-sensitive luminescent material,the model construction and the data processing. A system integration has been collocated for the image acquisition system,the optical system and the calibration system.The TSP technique becomes increasingly suitable and practicable to be used in shock tunnel due to the measurement and calibration system.With the high spatial resolution images,the TSP technique could show the heat-flux distribution of main surface area of a vehicle.According to the detailed information of heat transfer,further data analyses can be actualized such as differentiating flow pattern and pinpointing transition location of boundary layer.Furthermore,the results of TSP technique are in good agreement with that obtained by conventional point sensors measurement. The TSP technique has been successfully applied in the experiment research on the boundary layer transition,the aerothermal environment in local interference regions and the heat-transfer on hypersonic vehicles with complex configurations. Currently, TSP technique has been developed as an improvement of heat-transfer measurement method in addition to the traditional discrete point measurement method in CARDC.关键词
温敏漆/热流/激波风洞/传感器/图像/数据处理/边界层Key words
temperature sensitive paint/heat transfer/shock tunnel/sensor/image/data processing/boundary layer分类
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张扣立,周嘉穗,孔荣宗,马晓伟,江涛..CARDC 激波风洞 TSP 技术研究进展[J].空气动力学学报,2016,34(6):738-743,6.
