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论文:2013,Vol:31,Issue(4):517-521 |
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引用本文： |
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李盈盈, 周洲, 甘文彪. 多鼓包技术在超临界翼型上的减阻特性研究[J]. 西北工业大学 |
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Li Yingying, Zhou Zhou, Gan Wenbiao. Drag Reduction Research on Multi-Bump Technology for Supercritical Airfoil[J]. Northwestern polytechnical university |
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| 多鼓包技术在超临界翼型上的减阻特性研究 |
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| 李盈盈, 周洲, 甘文彪 |
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| 西北工业大学 无人机特种技术重点实验室, 陕西 西安 710065 |
| 摘要: |
| 针对超临界翼型的流动特征,利用计算流体力学方法,通过典型算例开展了对多鼓包技术流动机理与减阻特性的研究。首先对超临界翼型的绕流特征进行了分析,在流动发生转捩的前缘区域布置鼓包,改善翼型前段的压力梯度,减小湍流粘性,达到减阻的目的。然后在典型超临界翼型RAE2822上,研究了前缘鼓包与激波鼓包分别单独作用时,其几何外形和位置参数对减阻的影响。最后对前缘鼓包、激波鼓包的位置和形状参数进行了协同调整,研究了前缘鼓包对常用激波鼓包的减阻效果的影响。经计算,前后鼓包共同减阻的效果确实优于单独激波鼓包,最大减阻量可达11.5%。 |
| 关键词:
飞行器
翼型
CFD
减阻
升阻比
压力分布
流动机制
多鼓包
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| Drag Reduction Research on Multi-Bump Technology for Supercritical Airfoil |
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| Li Yingying, Zhou Zhou, Gan Wenbiao |
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| Science and Technology on UAV Laboratory, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| We study the flow characteristics of supercritical airfoil;we have tested some classic examples to explore the flow mechanism of multi-bump technology and to study the characteristics of drag reduction by taking advantage of Computational Fluid Dynamics (CFD) method.We analyze the flow mechanism of multi-bump and then adjust the location and the geometry of multi-block.We find that not only the bump near the shock can reduce the wave drag but also the bump located near the leading-edge can improve the flow properties of airfoil.We applied multi-bump technology to RAE2822,and we find that the multi-bump technology can get more drag reduction,and that the total drag reduction can reach 11.5%. |
| Key words:
aircraft
airfoils
computational fluid dynamics
drag reduction
lift darg ratio
pressure distribution
schematic diagrams
flow mechanism
multi-bump
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| 收稿日期: 2012-10-18
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 李盈盈(1990-),女,西北工业大学硕士研究生,主要飞行器设计研究。
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| 作者相关文章 |
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| 李盈盈 在本刊中的所有文章 |
| 周洲 在本刊中的所有文章 |
| 甘文彪 在本刊中的所有文章 |
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参考文献: |
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[2] 李沛峰, 张彬乾, 陈迎春.减小翼型激波阻力的鼓包流动控制技术.航空学报, 2011, 32(06): 971-977 Li Peifeng, Zhang Binqian, Chen Yingchun.Wave Drag Reduction of Airfoil with Shock Control Bump.Acta Aeronautica et Astronautica Sinica, 2011, 32(6): 971-977 (in Chinese)
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