A correction method of icing testing scaling law with dynamic effects

LI Weihao; LI Weibin; YI Xian; WANG Yingyu

doi:10.11729/syltlx20190166

Volume 34 Issue 3

Jun. 2020

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Article Navigation > Journal of Experiments in Fluid Mechanics > 2020 > 34(3): 97-103

LI Weihao, LI Weibin, YI Xian, et al. A correction method of icing testing scaling law with dynamic effects[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(3): 97-103. doi: 10.11729/syltlx20190166

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A correction method of icing testing scaling law with dynamic effects

doi: 10.11729/syltlx20190166

LI Weihao^1
,,
LI Weibin²,
YI Xian^{1
,
,},
WANG Yingyu²

1.
Key Laboratory of Icing and Anti/De-icing, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
Computational Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2019-12-09
Rev Recd Date: 2020-01-05
Publish Date: 2020-06-25

Abstract

Abstract

The icing scaling law is an important theoretical method for converting flight conditions into test conditions. But existing icing scaling laws are mostly based on small droplets, which can cause large errors when applied to scaling transformations of large droplets. In response to this situation, research on icing scaling law considering the dynamics of droplets was carried out. Firstly, based on the ONERA scaling laws, the scaling parameters of the droplet deformation/breakup and splash were incorporated, and the modified icing scaling law was proposed. Secondly, based on these two scaling laws, the numerical simulation method was used to calculate the collection coefficient before and after the correction. The validity of the correction method was verified. Finally, the variation of the test parameters obtained by the two correction methods with the size reduction ratio was analyzed. The application of the scaling law in the icing test was given. The results show that the proposed method improves the coincidence of the local collection coefficient and reduces the average error of the collection coefficient and the impact limit. In addition, the scaling test parameters are within the design range of the icing wind tunnel. These correction methods can provide guidance for scaling transformations in supercooled large droplets ice wind tunnel test.
- aircraft icing,
- scaling law,
- Supercooled Large Droplet (SLD),
- dynamic effect,
- numerical computation

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References(16)

References

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