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论文:2012,Vol:30,Issue(2):169-174 |
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引用本文： |
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关晓辉, 李占科, 宋笔锋. 基于FCE方法的超声速机翼厚度分布优化[J]. 西北工业大学 |
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Guan Xiaohui, Li Zhanke, Song Bifeng. Exploring Optimization of Supersonic Wing Thickness Distribution Using FCE (Far-field Composite Element) Method[J]. Northwestern polytechnical university |
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| 基于FCE方法的超声速机翼厚度分布优化 |
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| 关晓辉, 李占科, 宋笔锋 |
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| 西北工业大学 航空学院,陕西 西安 710072 |
| 摘要: |
| 远场组元(Far-field Composite Element,FCE)激波阻力优化方法是基于类别形状函数变换(Class Shape Transformation,CST)参数化方法发展出的一种超声速飞行器气动外形优化方法。文章使用CST参数化方法对超声速客机的大后掠机翼进行外形参数化,并以机翼容积和局部相对厚度为约束条件,使用FCE方法对其厚度分布进行以激波阻力最小为设计目标的快速优化。与原机翼相比,FCE优化方法使机翼激波阻力系数降低达61%,是超声速飞行器概念设计阶段降低激波阻力十分有用的优化方法。 |
| 关键词:
FCE
CST
超声速飞行器
减阻
参数化
外形优化
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| Exploring Optimization of Supersonic Wing Thickness Distribution Using FCE (Far-field Composite Element) Method |
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| Guan Xiaohui, Li Zhanke, Song Bifeng |
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| College of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China |
| Abstract: |
| Developed from the class shape transformation (CST) geometric parameterization method, the FCE wavedrag optimization method is a new aerodynamic shape optimization method for supersonic aircraft. We use the CSTparameterization method to perform the shape parameterization of a typical and large swept wing model of a super-sonic aircraft. Sections 1 and 2 of the full paper explain our exploration, whose core consists of: (1) under theconstraints of the total volume and local thicknesses of the swept wing, we carry out the quick optimization of thewing thickness distribution, aiming to achieve minimum wave drag; (2) we use the supersonic area rule to calcu-late the wave drag and to optimize the shape parameters of the swept wing with the Lagrange multiplier method, thusrequiring no iteration and reducing computation complexity. The optimization results, given in Table 1 and Figs. 4, 5 and 6, and their analysis show preliminarily that, compared with the baseline wing model, our optimization meth-od can reduce the wave drag coefficient by 61%, thus being a useful method for aerodynamic shape optimization soas to reduce the wave drag at the stage of the conceptual design of a supersonic aircraft. |
| Key words:
algorithms
calculations
computational complexity
computational geometry
conceptual design
con-strained optimization
drag coefficient
drag reduction
Lagrange multipliers
models
parameteriza-tion
shape optimization
shock waves
supersonic aerodynamics
supersonic aircraft
swept wings
thickness control
three dimensional
transport aircraft;Far-field Composite Element (FCE)
ClassShape Transformation (CST)
wave drag
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| 收稿日期: 2011-05-21
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 关晓辉(1987-),西北工业大学博士研究生,主要从事飞行器总体设计的研究。
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参考文献: |
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[1] Straathof M H, Van Tooren M J L, Voskuijl M, et al. Aerodynamic Shape Parameterisation and Optimisation of Novel Configu-rations. Proceedings of the RAeS Aerodynamic Shape Parameterisation and Optimisation of Novel Configurations Conference．London: Royal Aeronautical Soc, 2008:1-14
[2] Kulfan B M, Bussoletti J E．“Fundamental”Parametric Geometry Representations for Aircraft Component Shapes. AIAA-2006-6948, 2006
[3] Kulfan B M. Recent Extensions and Applications of the“CST”Universal Parametric Geometry Representation Method. AIAA-2007-7709
[4] Kulfan B M. A Universal Parametric Geometry Representation Method -“CST”. AIAA-2007-62
[5] Ceze M, Hayashi M, Volpe E. A Study of the CST Parameterization Characteristics. AIAA-2009-3767
[6] Jones R T. Theory of Wing-Body Drag at Supersonic Speeds. NACA-RM-A53H18A, 1953
[7] Nikolic V, Jumper E J. Zero-Lift Wave Drag Calculation Using Supersonic Area Rule and Its Modifications. AIAA-2004-217
[8] Kulfan B M. New Supersonic Wing Far-Field Composite-Element Wave-Drag Optimization Method , “FCE”. AIAA-2008-132 |
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