伴随压力分布反设计方法在大型客机气动优化中的初步探索

刘峰博; 蒋城; 马涂亮; 梁益华

doi:10.7527/S1000-6893.2019.23372

航空学报 >

2020 , Vol. 41 >Issue 5: 623372 - 623372

DOI: https://doi.org/10.7527/S1000-6893.2019.23372

飞行器气动外形数值优化与设计专栏

伴随压力分布反设计方法在大型客机气动优化中的初步探索

刘峰博 ,
蒋城 ,
马涂亮 ,
梁益华

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1. 中国航空工业西安航空计算技术研究所, 西安 710065;
2. 中国商飞上海飞机设计研究院, 上海 201210

收稿日期: 2019-08-12

修回日期: 2019-09-02

网络出版日期: 2019-09-30

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Aerodynamic optimization design of large civil aircraft using pressure distribution inverse design method based on discrete adjoint

LIU Fengbo ,
JIANG Cheng ,
MA Tuliang ,
LIANG Yihua

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1. AVIC Aeronautics Computing Technique Research Institute, Xi'an 710065, China;
2. COMAC Shanghai Aircraft Design and Research Institute, Shanghai 201210, China

Received date: 2019-08-12

Revised date: 2019-09-02

Online published: 2019-09-30

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摘要

从工程应用角度出发，对离散伴随压力分布反设计优化方法在宽体客机机翼设计中的应用进行了研究。提出了三维构型伴随压力分布反设计与伴随优化相结合的优化设计思路，促进了离散伴随气动优化设计方法的工程化。首先，针对CRM机翼构型进行了三维压力分布反设计，验证了离散伴随压力分布反设计在三维问题中的准确性和高效性。其次，应用提出的新的优化设计思路，在某宽体全机构型两点气动优化结果的基础上，引入压力分布反设计约束方法，改进了机翼压力分布和低马赫数的阻力蠕增特性，并取得了不错的减阻及阻力发散特性提升效果，提升了优化构型的工程适用性。

关键词： 气动优化设计; 离散伴随方法; 多设计点优化; 反设计; 超临界机翼

本文引用格式

刘峰博 , 蒋城 , 马涂亮 , 梁益华 . 伴随压力分布反设计方法在大型客机气动优化中的初步探索[J]. 航空学报, 2020 , 41(5) : 623372 -623372 . DOI: 10.7527/S1000-6893.2019.23372

Abstract

From the engineering application point of view, the application of the discrete adjoint companion pressure distribution inverse design optimization method in the design of wide-body civil aircraft wing is studied. The optimization design idea of three-dimensional configuration combined with pressure distribution inverse design and adjoint optimization is proposed, which promotes the engineering of discrete adjoint aerodynamic optimization design method. Firstly, the three-dimensional pressure distribution inverse design is carried out for the CRM wing configuration, which verifies the accuracy and efficiency of the discrete adjoint pressure distribution inverse design in the three-dimensional problem. Secondly, based on the new optimization design idea proposed by the application, the pressure distribution inverse design constraint method is introduced on the basis of a wide-body full-body two-point aerodynamic optimization result, and the wing pressure distribution and the resistance creep increase characteristic of the low Mach number are improved. And achieved good drag reduction and resistance divergence characteristics to improve the engineering applicability of the optimized configuration.

Key words： aerodynamic optimization design; discrete adjoint method; multipoint optimization; inverse design; supercritical wing

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