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论文:2014,Vol:32,Issue(4):517-522 |
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引用本文： |
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李占科, 张旭, 冯晓强, 关晓辉. 双向飞翼超声速客机激波阻力和声爆研究[J]. 西北工业大学 |
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Li Zhanke, Zhang Xu, Feng Xiaoqiang, Guan Xiaohui. Study on Drag and Sonic Boom of Supersonic Bi-Directional Flying Wing[J]. Northwestern polytechnical university |
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| 双向飞翼超声速客机激波阻力和声爆研究 |
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| 李占科, 张旭, 冯晓强, 关晓辉 |
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| 西北工业大学 航空学院, 陕西 西安 710072 |
| 摘要: |
| 基于超声速双向飞翼构型,采用CFD方法进行阻力计算,采用F-BOOM程序进行声爆计算,研究翼型、平面形状和EFCE激波阻力优化算法对双向飞翼激波阻力和声爆的影响。计算结果表明,平底构型可以明显降低双向飞翼超声速客机的超声速巡航的声爆,却很大程度上增加了巡航阻力,而对称构型却恰好相反;细长的平面几何形状对降低双向飞翼激波阻力和声爆都有作用,尤其对降低对称构型的声爆效果明显;EFCE激波阻力优化算法对降低双向飞翼激波阻力有明显作用,但同时会带来声爆方面的不利影响。因此,超声速客机的减阻设计和低声爆设计需要进行权衡研究。 |
| 关键词:
超声速客机
双向飞翼
激波阻力
声爆
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| Study on Drag and Sonic Boom of Supersonic Bi-Directional Flying Wing |
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| Li Zhanke, Zhang Xu, Feng Xiaoqiang, Guan Xiaohui |
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| College of Aeronautics, Northwestern Polytechnical University, Xian 710072, China |
| Abstract: |
| Based on SBiDir-FW (supersonic bi-directional flying wing ), CFD (Computational Fluid Dynamics ) method is used to calculate the drag and F-BOOM method is applied to compute the sonic boom;this study focuses on how the airfoil, flat shape and EFCE shock wave drag optimization algorithm affect the drag and sonic boom of SBiDir-FW. The results and their analysis show preliminarily that: (1 ) flat bottom configuration can reduce the cruise sonic boom of SBiDir-FW remarkably, but it greatly increases the cruising drag, while the opposite phenome-non can be detected in symmetrical configuration;(2)slender flat shape can reduce drag and sonic boom of SBiDir-FW, especially for reducing the sonic boom of symmetrical configuration;(3)EFCE shock wave drag optimization algorithm can reduce the shock wave drag of SBiDir-FW obviously, but will also bring adversely effect on sonic boom. Therefore, the balance should be weighed when considering the design of low drag and low sonic boom for supersonic aircraft. |
| Key words:
aerodynamic configurations
aerodynamic drag
algorithms
airfoils
angle of attack
calculations
computational fluid dynamics
design
Euler equations
flow fields
Lagrange multipliers
Mach number
mesh generation
optimization
pressure
schematic diagrams
shock waves
supersonic aircraft
wings
bi-directional flying wing
shock wave drag
sonic boom
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| 收稿日期: 2013-11-01
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 李占科(1974-),西北工业大学副教授,主要从事飞行器总体设计研究。
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