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Design of Hybrid Airfoils for Icing Tunnel Tests Based on Reduced-Order Modeling Methods

Authors
Shon, SoonhoKang, Yu-EopHong, YoonpyoYee, KwanjungMyong, R. S.
Issue Date
2022
Publisher
AMER INST AERONAUTICS ASTRONAUTICS
Citation
JOURNAL OF AIRCRAFT, v.59, no.4, pp.847 - 860
Indexed
SCIE
SCOPUS
Journal Title
JOURNAL OF AIRCRAFT
Volume
59
Number
4
Start Page
847
End Page
860
URI
https://scholarworks.bwise.kr/gnu/handle/sw.gnu/2730
DOI
10.2514/1.C036435
ISSN
0021-8669
Abstract
A hybrid airfoil is a scaled model for generating a full-scale ice shape for icing wind tunnel tests. This is possible by matching full-scale properties such as the distributions of collection efficiency and heat transfer coefficient. Previous studies have used indirect methods using full-scale stagnation point location or tangent droplet trajectories. Therefore, these methods can cause a discrepancy between the full-scale and hybrid airfoil ice shapes under glaze ice conditions. To cope with the issue, this paper proposes a new approach to match the distributions of the full-scale collection efficiency and heat transfer coefficient on the leading edge, using a viscous turbulent computational fluid dynamics icing simulation. For computational efficiency, reduced-order modeling based optimization was used to match the distributions. The optimization process was applied to the glaze ice condition with a high liquid water content and temperature. The results indicate that matching the distribution of the heat transfer coefficient is recommended to minimize the error between full-scale and hybrid airfoil ice shapes for the glaze ice condition. Finally, a hybrid airfoil flap geometry, which can be applied to various angles of attack, was designed using the optimization design process.
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대학원 (기계항공우주공학부)
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