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论文:2016,Vol:34,Issue(4):578-586 |
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引用本文： |
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沈广琛, 白俊强, 刘南, 刘睿. 新型机翼后缘变弯运动机构仿真及其气动影响研究[J]. 西北工业大学学报 |
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Shen Guangchen, Bai Junqiang, Liu Nan, Liu Rui. Mechanical Simulation and Aerodynamic Analysis on a New Type of Wing Trailing Edge Variable Camber[J]. Northwestern polytechnical university |
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| 新型机翼后缘变弯运动机构仿真及其气动影响研究 |
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| 沈广琛, 白俊强, 刘南, 刘睿 |
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| 西北工业大学 航空学院, 陕西 西安 710072 |
| 摘要: |
| 采用计算流体力学方法和CATIA DMU Kinematics机构仿真，对一套可用于目前及未来民用客机机翼后缘变弯的增升装置系统进行研究，主要包括襟翼运动机构和扰流板下偏。通过运动学分析，采用的襟翼机构可保证巡航阶段后缘变弯过程中机构上下表面无缝，同时满足起降过程对襟翼的运动轨迹的要求。相比简单铰链机构，应用该机构的起飞构型线性段升力系数增加0.05，升阻比的增加量在0.2%~3%范围内；着陆阶段扰流板下偏，较未偏转扰流板的最大升力系数增加1.14%，且线性段上移0.15，显示了该机构具有较高的增升效率。在二维翼型上应用该机构实现后缘变弯度，升阻比有较大提升，且根据来流马赫数的不同改变后缘弯度可以有效地提高阻力发散马赫数。在某远程宽体客机翼身组合体构型上应用该机构实现巡航阶段后缘变弯度，巡航升阻比的增加量在0.345%~2.28%范围内。综上所述，在不增加机构复杂性和重量的前提下，研究的新型机翼后缘变弯运动机构能够有效地提高气动效率。 |
| 关键词:
增升装置
空气动力学
机构
后缘变弯度
计算流体力学
气动构型
升阻比
马赫数
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| Mechanical Simulation and Aerodynamic Analysis on a New Type of Wing Trailing Edge Variable Camber |
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| Shen Guangchen, Bai Junqiang, Liu Nan, Liu Rui |
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| School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| By using computational fluid dynamics and CATIA DMU Kinematics, a high-lift system that could be used on the present and future civil aircraft for varying wing camber during cruise has been studied. It consists of flap mechanism and drooping spoiler. Kinematic analysis of the flap mechanism shows that there won't be any gap on the wing surface during cruise. Besides, the track of flap meets the requirements of takeoff and landing. Compared with the simple hinged flap, the linear range of lift coefficient of takeoff configurations that applied the flap mechanism increases by 0.05, and the corresponding increase of lift to drag ratio is from 3% to 0.2%. The maximum lift coefficient of landing configuration with drooping spoiler increases by 1.14% and the linear range of lift coefficient increases to 0.15 than the configuration without spoiler droop, which demonstrates its high efficiency. The flap mechanism has been used to change trailing edge camber on the basis of 2D cruise foils and the lift to drag ratio has been improved. The drag-divergence Mach number increases with trailing edge deflection angle. The flap mechanism has also been used to change trailing edge camber of a long-range, wide-body transport aircraft. In the entire range of lift coefficient available during cruise, the L/D of initial configuration has increased by 0.345%~2.28%. In conclusion, the high-lift system used for varying camber during cruise shows great benefits on aerodynamics without increasing complexity and weight of mechanism. |
| Key words:
high-lift system
aerodynamics
mechanisms
trailing edge variable camber
computational fluid dynamics
aerodynamic configurations
lift to drag ratio
Mach number
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| 收稿日期: 2016-03-08
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 沈广琛(1991-),西北工业大学硕士研究生,主要从事飞行器气动外形优化设计研究。
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| 相关功能 |
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| 作者相关文章 |
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| 沈广琛 在本刊中的所有文章 |
| 白俊强 在本刊中的所有文章 |
| 刘南 在本刊中的所有文章 |
| 刘睿 在本刊中的所有文章 |
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参考文献: |
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