气动

Research on Calculation Method of Aerodynamic Parameters of Supersonic Probe Based on Gas Compressibility Factor

  • ZHONG Jingjun ,
  • HUANG Gangfeng ,
  • WU Wanyang ,
  • KAN Xiaoxu
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  • Merchant Marine College, Shanghai Maritime University, 1550 Haigang Avenue, Pudong District, Shanghai 201306

网络出版日期: 2023-11-30

基金资助

This study was co-supported by the National Natural Science Foundation of China (No. 51906134 and 51436002).

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022

Research on Calculation Method of Aerodynamic Parameters of Supersonic Probe Based on Gas Compressibility Factor

  • ZHONG Jingjun ,
  • HUANG Gangfeng ,
  • WU Wanyang ,
  • KAN Xiaoxu
Expand
  • Merchant Marine College, Shanghai Maritime University, 1550 Haigang Avenue, Pudong District, Shanghai 201306

Online published: 2023-11-30

Supported by

This study was co-supported by the National Natural Science Foundation of China (No. 51906134 and 51436002).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022

摘要

超声速多孔气动探针是开展风洞实验的关键测试工具,有必要开展能够提高探针测量精度、扩展探针适用范围的基础性研究。本文理论推导出气体压缩因子δs~f(p*,psκλ)来扩展伯努利方程的适用范围,并讨论了使用气体压缩因子求解超声速气流速度和马赫数的可信度问题。研究结果表明:本文所提出的超声速气流的气动参数计算方法与气体动力学理论计算相比的计算误差在万分之一范围内,具有可信性。本文算法与其余三种算法相对比,对跨声速涡轮平面叶栅的试验数据求解超声速气流的速度和马赫数以及激波前后静压比的计算误差均在万分之一范围内,但是,激波后马赫数的误差相对较大。本文所提出的一种通用的超声速多孔气动探针自动化非对向测量方法,总体上是可信的,且充分考虑了激波因素,能够丰富完善气动探针理论体系,为超声速风洞实验提供理论指导和技术支撑。

本文引用格式

ZHONG Jingjun , HUANG Gangfeng , WU Wanyang , KAN Xiaoxu . Research on Calculation Method of Aerodynamic Parameters of Supersonic Probe Based on Gas Compressibility Factor[J]. 热科学学报, 2022 , 31(1) : 111 -119 . DOI: 10.1007/s11630-022-1514-9

Abstract

The supersonic multi-hole probe is an essential test tool for wind tunnel experiments, which is necessary to develop the basic research of improving the measurement accuracy and expanding the application of the probes.
This paper theoretically derived a gas compression factor δs~f(p*, ps, κ, λ) to expand the scope of application of Bernoulli’s equation, and discussed the reliability issues of using this factor to solve the velocity and Mach number of the supersonic flow. The research results show that the calculation method of aerodynamic parameters of the supersonic flow proposed in this paper has credibility within one ten-thousandth of the calculation error compared with the calculation of aerodynamic theory. Compared with the algorithm in this paper and the other three algorithms, the calculation errors of the velocity and Mach number of the supersonic flow and the static pressure ratio before and after the shock are all within the range of one ten-thousandth based on the experimental data of a transonic turbine linear cascade. However, the error of the post-wave Mach number is relatively large. Finally, a universal supersonic multi-hole probe calibration algorithm proposed in this paper is suitable for automated non-opposing measurement. It has generally credible and fully considers the shock wave factor. It will improve the theoretical system of multi-hole probes, and provide theoretical guidance and technical support for the supersonic wind tunnel experiment.

参考文献

[1] Vergine F., Maddalena L., Stereoscopic particle image velocimetry measurements of super-sonic, turbulent, and interacting streamwise vortices: challenges and application. Progress in Aerospace Sciences, 2014, 66: 1–16.
[2] Johansen E.S., Rediniotis O.K., Jones G., The compressible calibration of miniature multi-hole probes. Journal of Fluids Engineering, 2001, 123(1): 128–138. 
[3] Delhaye D., Paniagua G., Fernández Oro J.M., et al., Enhanced performance of fast-response 3-hole wedge probes for transonic flows in axial turbomachinery. Experiments in Fluids, 2011, 50(1): 163–177. 
[4] Payne F.M., Ng T.T., Nelson R.C., Seven-hole probe measurement of leading-edge vortex flows. Experiments in Fluids, 1989, 7(1): 1–8. 
[5] Sumner D., Heseltine J.L., Dansereau O.J.P., Wake structure of a finite circular cylinder of small aspect ratio. Experiments in Fluids, 2004, 37(5): 720–730. 
[6] Gilarranz J.L., Ranz A.J., Kopko J.A., et al., On the use of five-hole probes in the testing of industrial centrifugal compressors. Journal of Turbomachinery, 2005, 127(1): 91–106. 
[7] Kan X.X., Huang G.F., Wu W.Y., Zhong J.J., Research on solving flow velocity method of a high subsonic probe. Academic Conference on Thermomechanical and Aerodynamics of Chinese Society of Engineering Thermophysics; Baoding, Hebei, China, 2020, Oct 23–25, No. 202446. (in Chinese)
[8] Goodyer M.J., A stagnation pressure probe for supersonic and subsonic flows. Aeronautical Quarterly, 1974, 25(02): 91–100. 
[9] Hsieh T., Flow-field study about a hemi-sphere-cylinder in the transonic and low supersonic Mach number range. AIAA Paper, 1975, 75–83: 1–11. 
[10] Zhao B., Zhao J., Numerical simulation of pressure probe calibration based on CFD under supersonic condition. Metrology & Measurement Technology, 2017, 37(2): 15–18, 36. (in Chinese) 
[11] Pisasale A.J., Ahmed N.A., Theoretical calibration for highly three-dimensional low-speed flows of a five-hole probe. Measurement Science & Technology, 2002, 13(7): 1100. 
[12] Anderson J.D., Fundamentals of aerodynamics. Beijing: Aviation industry press, 2010, 3: 549–550. 
[13] Zhong J.J., Kan X.X., Wu W.Y., et al., A composite pressure-temperature probe and flow velocity calculation method. China, 202010599342.5.
[14] Luo W.W., Wang H.S., Zhao X.L., Experiment investigation on the flow characteristic in a transonic convergent-divergent turbine cascade. Journal of Engineering Thermophysics, 2013, 34(7): 1229–1233. (in Chinese)

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