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Simplified Method for Natural Laminar Flow Prediction on Supersonic Highly Swept Wings

文献类型：期刊论文

作者Nie, Han2; Liu, Wen2; Zhang, Chen-An2; Liu, Yang2; Guo, Shuai-Qi2; Song, Wen-Ping1; Han, Zhong-Hua1
刊名AIAA JOURNAL
出版日期2025-09-24
页码14
关键词Mean Aerodynamic Chord Friction Drag Reduction Wing Configurations Laminar to Turbulent Transition Supersonic Aircraft Drag Reduction Boundary Layer Transition Laminar Turbulent Transition Linear Stability Analysis Symbolic Artificial Intelligence
ISSN号0001-1452
DOI10.2514/1.J065216
通讯作者Liu, Wen(lw@imech.ac.cn) ; Liu, Yang(liuyang2@imech.ac.cn)
英文摘要Incorporating natural laminar flow (NLF) into aircraft preliminary design contributes to enhancing the performance of the next-generation supersonic transports. However, conducting shape design optimizations to analyze the achievable NLF extent and assess the drag reduction potential on supersonic wings is too time-consuming for preliminary designs. This paper proposes a simplified method to predict the achievable NLF extent on supersonic wings. First, linear stability analyses are conducted to calculate transition Reynolds numbers under an ideal pressure distribution. Second, the precalculated transition Reynolds numbers are used to establish a simplified model via symbolic regression. Next, the effects of Mach number, flight altitude, and sweep angle on the achievable NLF regions of supersonic wings are investigated based on the established model. Results show that a higher flight altitude and a freestream Mach number around 1.7 are favorable for enlarging the laminar extent. A decrease of wing leading-edge sweep angle leads to a higher transition Reynolds number but not necessarily to an expanded NLF region. Accordingly, an alternative parameter, the laminar flow length, is proposed to characterize the laminar extent on a wing instead of the transition Reynolds number, and the laminar extents for conventional NLF designs and novel crossflow-attenuated NLF designs are presented.
WOS关键词DESIGN
资助项目Chinese Academy of Sciences Project for Young Scientists in Basic Research ; Strategic Priority Research Program of Chinese Academy of Science[XDB0620402] ; Youth Innovation Promotion Association CAS[2023023] ; [YSBR-107]
WOS研究方向Engineering
语种英语
WOS记录号WOS:001579097700001
资助机构Chinese Academy of Sciences Project for Young Scientists in Basic Research ; Strategic Priority Research Program of Chinese Academy of Science ; Youth Innovation Promotion Association CAS
源URL[http://dspace.imech.ac.cn/handle/311007/104101]  
专题力学研究所_高温气体动力学国家重点实验室
通讯作者Liu, Wen; Liu, Yang
作者单位1.Northwestern Polytech Univ, Sch Aeronaut, Natl Key Lab Aircraft Configurat, Xian 710072, Peoples R China
2.Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China
推荐引用方式
GB/T 7714		 Nie, Han,Liu, Wen,Zhang, Chen-An,et al. Simplified Method for Natural Laminar Flow Prediction on Supersonic Highly Swept Wings[J]. AIAA JOURNAL,2025:14.
APA Nie, Han.,Liu, Wen.,Zhang, Chen-An.,Liu, Yang.,Guo, Shuai-Qi.,...&Han, Zhong-Hua.(2025).Simplified Method for Natural Laminar Flow Prediction on Supersonic Highly Swept Wings.AIAA JOURNAL,14.
MLA Nie, Han,et al."Simplified Method for Natural Laminar Flow Prediction on Supersonic Highly Swept Wings".AIAA JOURNAL (2025):14.

入库方式： OAI收割

来源：力学研究所

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