Integral Airfoil Generation of Multi-rotor Aircraft Based on Optimization of Upper Wing Contour and CFD Simulation
سال انتشار: 1403
نوع سند: مقاله ژورنالی
زبان: انگلیسی
مشاهده: 27
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شناسه ملی سند علمی:
JR_JAFM-17-5_014
تاریخ نمایه سازی: 7 اسفند 1402
چکیده مقاله:
Regarding the airfoil optimization design of multi-rotor unmanned aerial vehicles, this paper proposes an integral airfoil design method based on upper airfoil contour optimization. Firstly, by designing concave descent input curves with ۰-۱ distribution, the upper arc of different optimized airfoils is obtained using the Tangent circles method. Secondly, an integral airfoil generation method is developed after establishing the middle arc. As the upper and lower arcs of different shapes are randomly combined, various airfoil profiles are obtained by random assortment. Finally, the effectiveness and accuracy of the designed airfoil are validated through Python programming. The airfoil is generated by the XFOIL program, and the optimal airfoil is output with a lift-to-drag ratio as the target. Meanwhile, an accurate Fluent analysis model is established, and a comparison verification is conducted on the data with the attack angle falling within [-۸.۰۲, ۱۲.۰۴] and lift-to-drag ratio falling within [-۵۰, ۱۰۰]. After Fluent modeling of the designed airfoil, the Euclidean distance between the calculated angle-lift-drag ratio data curve and the data curve tested by the wind tunnel is ۰.۰۳۳۱, while the Euclidean distance between the simulated data in the literature and the wind tunnel data is ۰.۰۴۰۸. It indicates that our precise model achieves ۱۸.۹% higher accuracy than the literature model. Testing and verification results indicate that our designed airfoil based on upper arc optimization and its corresponding airfoil library can meet the design requirements for the aerodynamic performance of airfoils in practical applications. It provides a valuable reference for the development of airfoil design, optimization, and generation methods.
کلیدواژه ها:
Airfoil design ، Parameterization method ، Upper airfoil contour optimization ، Computational fluid dynamics ، Aerodynamic performance
نویسندگان
Z. Wang
Army Command Academy of PLA, Jiangsu Nanjing ۲۱۰۰۴۵, China
Y. Zhu
Army Engineering University of PLA, Nanjing, Jiangsu, ۲۱۰۰۰۷, China
Q. Yuan
Southwest University of Science and Technology, Mianyang, Sichuan, ۶۲۱۰۱۰, China
W. B. Gu
Army Engineering University of PLA, Nanjing, Jiangsu, ۲۱۰۰۰۷, China
X. B. Xie
Army Engineering University of PLA, Nanjing, Jiangsu, ۲۱۰۰۰۷, China
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