飞翼布局翼型系列设计进展

张伟; 赵轲; 夏露; 高正红

doi:10.7638/kqdlxxb-2021.0282

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飞翼布局翼型系列设计进展

翼型研究新进展 | 更新时间：2026-05-28

- 飞翼布局翼型系列设计进展
- A multi-disciplinary global/local optimization method for flying-wing airfoils design
- 空气动力学学报 2021年39卷第6期页码：37-52
- 作者机构：
  
  西北工业大学航空学院,西安,710072
- 作者简介：
  
  张伟（1993-），男，黑龙江人，博士生，研究方向：飞行器设计. E-mail：18792896768@163.com
  高正红*，教授，研究方向：空气动力学. E-mail：zgao@nwpu.edu.cn
- 基金信息：
  
  翼型、叶栅国家重点实验室基金（6142201200106）
- DOI：10.7638/kqdlxxb-2021.0282
  中图分类号： V224
- 纸质出版：2021
- 稿件说明：
移动端阅览
张伟, 赵轲, 夏露, 等. 飞翼布局翼型系列设计进展[J]. 空气动力学学报, 2021, 39(6): 37−52.

ZHANG Wei, ZHAO Ke, XIA Lu, et al. A multi-disciplinary global/local optimization method for flying-wing airfoils design[J]. 2021, 39(6): 37-52.
张伟, 赵轲, 夏露, 等. 飞翼布局翼型系列设计进展[J]. 空气动力学学报, 2021, 39(6): 37−52. DOI： 10.7638/kqdlxxb-2021.0282

ZHANG Wei, ZHAO Ke, XIA Lu, et al. A multi-disciplinary global/local optimization method for flying-wing airfoils design[J]. 2021, 39(6): 37-52. DOI： 10.7638/kqdlxxb-2021.0282.

摘要

针对飞翼无尾布局飞机开展了基础翼型研究。归纳了飞翼布局翼型的设计特点和研究进展，提炼了飞翼无尾布局复杂的气动设计需求，总结了其展向气动分布特点，根据不同分区提出了翼型气动设计要求，并建立了分区翼型设计模型，形成了飞翼布局分区翼型系列。由于传统翼型设计模型未能考虑横流效应，导致翼型设计结果应用到三维布局上不能达到理想效果，提出了“全局+局部”的翼型多学科设计方法，根据飞翼布局分区翼型气动设计要求，建立了基于分区翼型设计模型的高效代理模型全局优化设计与三维布局环境下多剖面翼型局部优化设计的多学科协同设计方法。这种“全局+局部”的设计方法能够快速实现满足飞翼布局分区多剖面、多种性能要求的翼型设计，有效提高了设计翼型的性能与设计效率。最后以类X47-B布局为例，进行了翼型系列设计，验证了该方法的可靠性。

Abstract

This paper proposes a new design method for aircrafts with flying-wing layouts. Aerodynamic characteristics and design requirements of flying-wing layouts are firstly analyzed. Aerodynamic design requirements for different spanwise partitions of flying wings are then put forward for the design of partitioned airfoils. Since traditional airfoil design methods do not take the cross-flow effect into account

their applications in designing three-dimensional airfoil layouts cannot achieve desired performance. Consequently

a global/local airfoil multidisciplinary design method is proposed. According to aerodynamic design requirements of flying wings

an efficient proxy model based on partitioned airfoils for global optimization design and a refined local optimization design method for three-dimensional layouts are established and integrated. This multi-disciplinary collaborative global/local optimization method can quickly realize the airfoil design that meets the performance requirements of multi-section flying wing layouts

and can effectively improve the performance and design efficiency of designed airfoils. Finally

the reliability of this method is verified by an airfoil design process based on the X47-B layout.

关键词

Keywords

references

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