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论文:2018,Vol:36,Issue(2):203-210 |
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引用本文： |
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李沛峰, 张彬乾, 陶于金, 陈真利, 李栋. 翼身融合布局中央机体翼型设计研究[J]. 西北工业大学学报 |
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Li Peifeng, Zhang Binqian, Tao Yujin, Chen Zhenli, Li Dong. Center Body Airfoil Design for Blended Wing Body Configuration[J]. Northwestern polytechnical university |
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| 翼身融合布局中央机体翼型设计研究 |
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| 李沛峰1, 张彬乾2, 陶于金1, 陈真利2, 李栋2 |
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1. 西北工业大学 无人机研究所, 陕西 西安 710065;
2. 西北工业大学 航空学院, 陕西 西安 710072 |
| 摘要: |
| 针对翼身融合布局中央机体翼型设计，在满足总体装载约束条件下，研究对称翼型、后卸载翼型、前加载翼型和前加载-后卸载翼型的气动影响规律。150座级BWB布局研究结果表明，采用对称翼型时，外翼需采用较大的负几何扭转角以实现静稳定设计状态下的正零升力矩，但升阻性能损失较大；采用前加载翼型时，受布局平面形状限制，不易达到正零升力矩；采用后卸载翼型或前加载-后卸载翼型时，合理设计前加载或后卸载的区域及大小，可获得升阻及力矩特性较为理想的气动设计结果。翼身融合飞翼布局无人机应用研究表明，采用具有前加载特征的"鹰勾"隐身前缘设计，气动性能损失小。 |
| 关键词:
翼身融合布局
翼型
CFD
民机
无人机
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| Center Body Airfoil Design for Blended Wing Body Configuration |
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| Li Peifeng1, Zhang Binqian2, Tao Yujin1, Chen Zhenli2, Li Dong2 |
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1. Institute of UAV, Northwestern Polytechnical University, Xi'an 710065, China;
2. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| To design the center-body airfoil of a blended wing body configuration, the aerodynamic effects of the symmetrical airfoil, trailing-edge reflexed airfoil, leading-edge loaded airfoil and leading-edge loaded plus trailing-edge reflexed airfoil are investigated based on the constraints of system arrangement. A 150-passenger BWB configuration is studied; for a center-body with symmetrical airfoil, the larger outer-wing geometrical twist should be used to fulfill the positive zero-lift pitching moment according to the design requirements of longitudinal static stability, however, lift to drag ratio shows a big decrease. For leading-edge loaded airfoil, it is difficult to achieve a positive zero-lift pitching moment because of the platform limitation. For trailing-edge reflexed airfoil or leading-edge loaded plus trailing-edge reflexed airfoil, it is easy to achieve ideal design results when reasonably designing the leading-edge loading and trailing-edge unloading. The application of a blended wing body UAV shows that the loss of aerodynamic characteristics is small when adopting the "eagle hook" stealth leading edge that has the characteristics of leading edge loading. |
| Key words:
airfoils
wings
computational fluid dynamics
design
aerodynamic configurations
lift drag ratio
blended wing body
civil transport
unmanned aerial vehicles(UAV)
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| 收稿日期: 2017-05-26
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 李沛峰(1982-),西北工业大学助理研究员,主要从事飞行器设计及空气动力学研究。
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参考文献: |
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