Precise stagnation point heat flux measurement technique of sharp leading edges

Zhang Yang; Jia Guangsen; Sha Xinguo; Chen Xing

doi:10.11729/syltlx20180112

Volume 33 Issue 6

Dec. 2019

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Journal of Experiments in Fluid Mechanics > 2019 > 33(6): 59-64. > DOI: 10.11729/syltlx20180112

Zhang Yang, Jia Guangsen, Sha Xinguo, Chen Xing. Precise stagnation point heat flux measurement technique of sharp leading edges[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(6): 59-64. DOI: 10.11729/syltlx20180112

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Precise stagnation point heat flux measurement technique of sharp leading edges

1.
Beijing Institute of Space Long March Vehicle, Beijing 100076, China
2.
China Academy of Aerospace Aerodynamics, Beijing 100074, China

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Received Date: August 24, 2018
Revised Date: December 24, 2018

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Abstract

In order to improve the aerodynamic performance, a sharp leading edge is widely used in the hypersonic flight vehicles, which exerts a huge challenge on thermal protection systems. The sharpness of the leading edge makes it hard to measure the stagnation point heat flux precisely. In this paper, an integral sensor with high spatial resolution is developed to measure the stagnation point heat flux, and the corresponding estimation method is adopted as well. A wedge model with an interchangeable nose(R=1.0, 2.0 and 5.0 mm) is employed to validate the effectiveness of the sensor, and a series of experiments are conducted at the FD-20 impulse wind tunnel under the condition of Mach number of 4, 5, 6 and 8. The results indicate that the difference of the stagnation point heat flux values is less than 15% between experimental measurement and theoretical prediction.
- sharp leading edges,
- stagnation point heat flux,
- wind tunnel testing,
- parameter identification

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