Design of a standard aerodynamic model CHN-T2 for wide-body aircraft

LIU Hongyang; ZHOU Zhu; YU Yonggang; HUANG Jiangtao; TANG Yu; SONG Chao; LAN Qingsheng

doi:10.7638/kqdlxxb-2023.0026

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Design of a standard aerodynamic model CHN-T2 for wide-body aircraft

更新时间：2026-05-28

- Design of a standard aerodynamic model CHN-T2 for wide-body aircraft
- Vol. 41, Issue 10, Pages: 15-29(2023)
- 作者机构：
  
  1. 中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
  2. 中国空气动力研究与发展中心空天技术研究所,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0026
  CLC： V211.78
- Published：2023
- 稿件说明：
移动端阅览
刘红阳, 周铸, 余永刚, 等. 宽体客机气动标模CHN-T2设计[J]. 空气动力学学报, 2023, 41(10): 15−29.

LIU Hongyang, ZHOU Zhu, YU Yonggang, et al. Design of a standard aerodynamic model CHN-T2 for wide-body aircraft[J]. 2023, 41(10): 15-29.
刘红阳, 周铸, 余永刚, 等. 宽体客机气动标模CHN-T2设计[J]. 空气动力学学报, 2023, 41(10): 15−29. DOI： 10.7638/kqdlxxb-2023.0026

LIU Hongyang, ZHOU Zhu, YU Yonggang, et al. Design of a standard aerodynamic model CHN-T2 for wide-body aircraft[J]. 2023, 41(10): 15-29. DOI： 10.7638/kqdlxxb-2023.0026.

摘要

发展商用运输机标模是我国独立发展具有自主知识产权的先进民用飞机的重要支撑手段，对验证CFD技术和确认风洞试验品质具有重要意义。结合国内外主流宽体商业客机的布局特点和气动设计需求，基于自主开发的AMDEsign设计平台，设计研发了宽体客机标模CHN-T2。标模设计马赫数0.85，设计升力系数0.48。模型充分体现了主流宽体商用客机典型的双通道机身/超临界机翼/平立尾/翼吊通气短舱等几何特征，具有典型的部件间强干扰/激波分离/转捩等流场特征以及优异的高亚声速巡航/高升阻比气动效率等性能特征。通过气动外形优化设计、短舱吊挂组件影响及雷诺数效应等研究，并结合风洞试验数据对比分析，最终确认CHN-T2模型巡航升阻比达到21.8、阻力发散马赫数约为0.872、抖振边界大于1.3倍巡航升力系数、风洞试验准雷诺数为3 × 10

。研究认为，CHN-T2模型具有良好的气动性能，能够作为先进宽体客机气动标模进行应用推广。通过持续建立的丰富气动数据库和流场影像，可有力支撑宽体客机流动机理分析、CFD技术验证与确认、先进风洞试验技术发展验证、CFD与风洞数据相关性等研究。

Abstract

The development of commercial transport aircraft standard model is an important support for developing advanced civil aircraft with independent intellectual property rights

as well as the verification of CFD technique and wind tunnel test quality. Combined with the layout characteristics and aerodynamic design requirements of mainstream wide-body commercial aircrafts at home and abroad

a standard model CHN-T2 for the wide-body aircraft is designed based on the self-developed design platform AMDesign. The design Mach number is 0.85

and t

he design lift coefficient is 0.48. The CHN-T2 model can fully represent typical geometric characteristics of mainstream wide-body aircraft

such as the twin-aisle fuselage

supercritical wing

horizontal/vertical tail wing

and wing suspension nacelle. CHN-T2 has typical flow characteristics such as strong interference between components

shock wave separation

boundary layer transition

etc. It also has excellent performance characteristics such as high subsonic cruise and high lift-drag-ratio aerodynamic efficiency. Aerodynamic shape optimization design

nacelle suspension component influence

Reynolds number effect and wind tunnel test are carried out in the present study. The results show that the cruising lift-drag-ratio of the CHN-T2 model reaches 21.8

the drag divergence Mach number is about 0.872

the buffeting boundary is greater than 1.3 times the cruising lift coefficient

and the quasi Reynolds number in wind tunnel tests is 3×10

. The CHN-T2 model has excellent aerodynamic performance and can be applied as an advanced aerodynamic standard model for wide-body aircraft. By continuously enriching the aerodynamic database and flow field images

the model can effectively support the analysis of flow mechanisms for wide-body aircraft

CFD technique verification and confirmation

advanced wind tunnel test technique development

and correlation research between CFD and wind tunnel test data.

关键词

Keywords

references

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