›› 2014, Vol. 23 ›› Issue (10): 104702-104702.doi: 10.1088/1674-1056/23/10/104702

• ELECTROMAGNETISM, OPTICS, ACOUSTICS, HEAT TRANSFER, CLASSICAL MECHANICS, AND FLUID DYNAMICS • 上一篇    下一篇

Experimental study on supersonic film cooling on the surface of a blunt body in hypersonic flow

付佳, 易仕和, 王小虎, 何霖, 葛勇   

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
  • 收稿日期:2013-11-19 修回日期:2014-03-09 出版日期:2014-10-15 发布日期:2014-10-15
  • 基金资助:
    Project supported by the National Natural Science Foundation of China (Grant No. 11172326) and the Scientific Research Program of National University of Defense Technology, China (Grant No. 0100010112001).

Experimental study on supersonic film cooling on the surface of a blunt body in hypersonic flow

Fu Jia (付佳), Yi Shi-He (易仕和), Wang Xiao-Hu (王小虎), He Lin (何霖), Ge Yong (葛勇)   

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
  • Received:2013-11-19 Revised:2014-03-09 Online:2014-10-15 Published:2014-10-15
  • Contact: Yi Shi-He E-mail:yishihe@gfkd.edu.cn,_yishihe@nudt.edu.cn
  • About author:47.15.gm; 44.10.+i; 47.55.pb; 47.27.te
  • Supported by:
    Project supported by the National Natural Science Foundation of China (Grant No. 11172326) and the Scientific Research Program of National University of Defense Technology, China (Grant No. 0100010112001).

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摘要： The experimental study focuses on the heat flux on a double cone blunt body in the presence of tangential-slot supersonic injection into hypersonic flow. The tests are conducted in a contoured axisymmetric nozzle with Mach numbers of 7.3 and 8.1, and the total temperature is about 900 K. The injection Mach number is 3.2, and total temperature is 300 K. A constant voltage circuit is developed to supply the temperature detectors instead of the normally used constant current circuit. The schlieren photographs are presented additionally to visualize the flow and help analyze the pressure relationship between the cooling flow and the main flow. The dependence of the film-cooling effectiveness on flow parameters, i.e. the blow ratio, the convective Mach number, and the attack angle, is determined. A semi-empirical formula is tested by the present data, and is improved for a better correlation.

关键词: slot film cooling, hypersonic, schlieren visualization, cooling effectiveness

Abstract: The experimental study focuses on the heat flux on a double cone blunt body in the presence of tangential-slot supersonic injection into hypersonic flow. The tests are conducted in a contoured axisymmetric nozzle with Mach numbers of 7.3 and 8.1, and the total temperature is about 900 K. The injection Mach number is 3.2, and total temperature is 300 K. A constant voltage circuit is developed to supply the temperature detectors instead of the normally used constant current circuit. The schlieren photographs are presented additionally to visualize the flow and help analyze the pressure relationship between the cooling flow and the main flow. The dependence of the film-cooling effectiveness on flow parameters, i.e. the blow ratio, the convective Mach number, and the attack angle, is determined. A semi-empirical formula is tested by the present data, and is improved for a better correlation.

Key words: slot film cooling, hypersonic, schlieren visualization, cooling effectiveness

中图分类号:  (Thin film flows)

  • 47.15.gm
44.10.+i (Heat conduction) 47.55.pb (Thermal convection) 47.27.te (Turbulent convective heat transfer)