Design of Hybrid Airfoils for Icing Tunnel Tests Based on Reduced-Order Modeling Methods
- Authors
- Shon, Soonho; Kang, Yu-Eop; Hong, Yoonpyo; Yee, Kwanjung; Myong, R. S.
- Issue Date
- Jul-2022
- Publisher
- American Institute of Aeronautics and Astronautics
- Citation
- Journal of Aircraft, v.59, no.4, pp 847 - 860
- Pages
- 14
- Indexed
- SCIE
SCOPUS
- Journal Title
- Journal of Aircraft
- Volume
- 59
- Number
- 4
- Start Page
- 847
- End Page
- 860
- URI
- https://scholarworks.gnu.ac.kr/handle/sw.gnu/2730
- DOI
- 10.2514/1.C036435
- ISSN
- 0021-8669
1533-3868
- 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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Collections - 공학계열 > 기계항공우주공학부 > Journal Articles
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