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

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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.

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Abbreviations

a :

sound velocity

h :

gas enthalpy

K:

calibration coefficient

Ma :

Mach number

P :

pressure

q :

heat transfer per unit mass of fluid

T :

flow temperature

v :

flow velocity

γ :

specific heat ratio

δ s :

gas compression factor

ε(λ):

aerodynamic function of density

κ :

adiabatic index

λ :

velocity factor

π(λ):

aerodynamic function of pressure

ρ :

flow density

τ(λ):

aerodynamic function of temperature

s:

static value

α :

angle of pitch

β :

deflection angle

1:

before the shock wave

2:

behind the shock wave

*:

total value

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Acknowledgments

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

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Authors and Affiliations

  1. Merchant Marine College, Shanghai Maritime University, 1550 Haigang Avenue, Pudong District, Shanghai, 201306, China

    Jingjun Zhong, Gangfeng Huang, Wanyang Wu & Xiaoxu Kan

Authors
  1. Jingjun Zhong
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  2. Gangfeng Huang
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  3. Wanyang Wu
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  4. Xiaoxu Kan
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Corresponding author

Correspondence to Xiaoxu Kan.

Additional information

Article type: Contributed by Asian Congress on Gas Turbines 2020 (August 18–19, 2021, China).

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Zhong, J., Huang, G., Wu, W. et al. Research on Calculation Method of Aerodynamic Parameters of Supersonic Probe Based on Gas Compressibility Factor. J. Therm. Sci. 31, 111–119 (2022). https://doi.org/10.1007/s11630-022-1514-9

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  • DOI: https://doi.org/10.1007/s11630-022-1514-9

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