Study on the influence of cold spot effect on the thermal measurement characteristics of circular foil heat flow sensor in hypersonic convection environment

Li Yu; Zhu Guangsheng; Nie Chunsheng; Tan Meijing; Chen Weihua; Cao Zhanwei

doi:10.11729/syltlx20180110

Volume 33 Issue 4

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Article Navigation > Journal of Experiments in Fluid Mechanics > 2019 > 33(4): 39-44

Li Yu, Zhu Guangsheng, Nie Chunsheng, et al. Study on the influence of cold spot effect on the thermal measurement characteristics of circular foil heat flow sensor in hypersonic convection environment[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(4): 39-44. doi: 10.11729/syltlx20180110

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Study on the influence of cold spot effect on the thermal measurement characteristics of circular foil heat flow sensor in hypersonic convection environment

doi: 10.11729/syltlx20180110

1.
Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China
2.
China Academy of Launch Vehicle Technology, Beijing 100076, China

Received Date: 2018-07-26
Rev Recd Date: 2019-04-16
Publish Date: 2019-08-25

Abstract

Abstract

When a circular foil heat flux sensor is used to measure aerodynamic heating in a hypersonic convection environment, the surface temperature of the sensor is often lower than the surface temperature of the measured object. This surface temperature discontinuity would affect the flow of the boundary layer, which could distort the heat flux measurement result. For a blunt-head plate model, the numerical simulation method was used to study the formation mechanism of the "cold-spot effect" and the influence of the local low temperature of the sensor surface on the surface heat flux under hypersonic flow conditions. The results show that:the higher H_w/H_re is, which represents the ratio of the surface enthalpy of the measured object to the recovery enthalpy of the flow, the more obvious the "cold-spot effect" is; the lower T_w2/T_w1 is, which represents the ratio of the sensor surface temperature to the measured surface temperature, the more obvious the "cold-spot effect" is; the flow Reynolds number Re has less effect on the cold spot effect. The deviation of measurement results in response to the "cold spot effect" is analyzed under the condition of Mach 18 flow. The results show that the "cold spot effect" can make the measurement result 1.25 times higher, which reproduces the difference between the heat flow prediction results and the test results.
- hypersonic,
- convection,
- heat flux sensor,
- cold spot effect,
- numerical simulation

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References

[1]	中国科学院.新型飞行器中的关键力学问题[M].北京:科学出版社, 2008.
[2]	余平, 段毅, 尘军.高超声速飞行的若干气动问题[J].航空学报, 2015, 36(1):7-23. http://d.old.wanfangdata.com.cn/Periodical/hkxb201501003 Yu P, Duan Y, Chen J. Some aerodynamic issues in hypersonic flight[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):7-23. http://d.old.wanfangdata.com.cn/Periodical/hkxb201501003
[3]	James L D, Howard S C. Analysis of base pressure and base heating on a 5 degree half-angle cone in free flight near Mach 20(Reentry F)[R]. NASA-TM-X-2468, 1972.
[4]	Muylaert J, Cipollini F, Walpot L, et al. In flight research on real gas effects using the ESA EXPERT vehicles[R]. AIAA 2003-6981, 2003.
[5]	中国运载火箭技术研究院北京强度环境研究所.结构热试验技术[M].北京:宇航出版社, 2008.
[6]	丁小恒.高超声速飞行试验热流密度测量方法与装置研究[D].哈尔滨: 哈尔滨工业大学, 2017. http://cdmd.cnki.com.cn/Article/CDMD-10213-1016739227.htm Ding X H. Research on measuring method and device of heat flux in hypersonic flight test[D]. Harbin: Harbin Institute of Technology, 2017. http://cdmd.cnki.com.cn/Article/CDMD-10213-1016739227.htm
[7]	Rubesin M W. The effects of an arbitrary surface-temperature variation along a flat plate on the convective heat transfer in an incompressible turbulent boundary layer[R]. NACA-TN-2345, 1951.
[8]	Reynolds W C, Kays W M, Klein S J. Heat transfer in the turbulent incompressible boundary layer. Ⅱ-step wall-temperature distribution[R]. NASA Memo 12-2-58W, 1958.
[9]	Reynolds W C, Kays W M, Klein S J. A summary of experiments on turbulent heat transfer from a nonisothermal flat plate[J]. Journal of Heat Transfer, 1960, 82(4):341-348.
[10]	Conti R J. Heat-transfer measurements at Mach number of 2 in a turbulent boundary layer on a flat plate having a stepwise temperature distribution[R]. NASA-TN-D-159, 1959.
[11]	Hornbaker D R, Rall D L. Thermal perturbations caused by heat-flux transducers and their effect on the accuracy of heating-rate measurements[J]. ISA Transactions, 1964, 3(2):123-130.
[12]	Eckert E R G, Drake R M Jr. Analysis of heat and mass transfer[M]. 2nd ed. New York:McGraw-Hill, 1972.
[13]	Neumann R D. Thermal instrumentation: a state-of-the-art review[R]. WL-TR-96-2107, 1996.
[14]	Diller T E. Advances in heat flux measurements[J]. Advances in Heat Transfe, 1993, 23:279-368. http://d.old.wanfangdata.com.cn/Periodical/stxb201808003
[15]	Kandula M, Reinarts T. Corrections for convective heat flux gauges subjected to a surface temperature discontinuity[R]. AIAA-2002-3087, 2002.
[16]	Mukerji D, Eaton J K, Moffat R J. Convective heat transfer near one-dimensional and two-dimensional wall temperature steps[J]. Journal of Heat Transfer, 2004, 126(2):202-210. http://d.old.wanfangdata.com.cn/NSTLQK/NSTL_QKJJ0212045027/