CAE-AVM标模巡航构型的设计和数据库应用

华俊; 钟敏; 郑遂; 王钢林; 王浩; 白俊强

doi:10.7638/kqdlxxb-2022.0012

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CAE-AVM标模巡航构型的设计和数据库应用

专栏——民机气动标模CAE-AVM及相关研究进展 | 更新时间：2026-05-28

- CAE-AVM标模巡航构型的设计和数据库应用
- Design and database applications of CAE-AVM model cruise configuration
- 空气动力学学报 2022年40卷第4期页码：133-147
- 作者机构：
  
  1. 中国航空研究院,北京,100012
  2. 西北工业大学,西安,710072
- 作者简介：
  
  华俊，男，教授，研究方向：空气动力学，飞机设计. E-mail：huaj@cae.ac.cn
  钟敏*，高级工程师，研究方向：设计空气动力学. E-mail：zhongmin@cae.ac.cn
- 基金信息：
  
  中航工业创新基金
- DOI：10.7638/kqdlxxb-2022.0012
  中图分类号： V211.4
- 纸质出版：2022
- 稿件说明：
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华俊, 钟敏, 郑遂, 等. CAE-AVM标模巡航构型的设计和数据库应用[J]. 空气动力学学报, 2022, 40(4): 133−147.

HUA Jun, ZHONG Min, ZHENG Sui, et al. Design and database applications of CAE-AVM model cruise configuration[J]. 2022, 40(4): 133-147.
华俊, 钟敏, 郑遂, 等. CAE-AVM标模巡航构型的设计和数据库应用[J]. 空气动力学学报, 2022, 40(4): 133−147. DOI： 10.7638/kqdlxxb-2022.0012

HUA Jun, ZHONG Min, ZHENG Sui, et al. Design and database applications of CAE-AVM model cruise configuration[J]. 2022, 40(4): 133-147. DOI： 10.7638/kqdlxxb-2022.0012.

摘要

受计算流体力学（CFD）与风洞数据相关性研究以及新型远程飞机设计能力建设等需求驱动，巡航马赫数0.85量级气动标模的研发日益得到重视，并受益于先进CFD方法和风洞精细化试验验证技术的发展，得以顺利开展。本文介绍了民机标模CAE-AVM巡航构型及其原准机的总体布局和气动方案设计，给出了远程商务飞机和该速域下气动标模的设计特点分析，提出了气动标模风洞试验的特别要求和解决方案。文章同时给出了CFD与风洞数据的对比验证结果，以及CAE-AVM标模数据库建设状况和典型应用案例。研究表明，CAE-AVM标模在马赫数0.85、升力系数0.5、雷诺数2×10

的设计状态下，升阻比为17.6，抖振升力系数和阻力发散马赫数等参数均满足设计要求。研究中实现了同步测力、测压、测变形和测转捩的精细化试验技术，试验前针对包含模型机翼气动弹性变形和支撑机构的真实试验外形的CFD预评估有效提高了试验效率。CAE-AVM数据库及其在CFD软件验证、CFD-风洞数据相关性研究、风洞动态和精细化试验技术开发以及民机设计分析方面的应用，表明了共用标模的必要性和实用性。

Abstract

Driven by the need of CFD (Computational Fluid Dynamics)-wind tunnel data correlation research and new long-haul aircraft development

the aerodynamic standard model at a cruise Mach number of 0.85 has drawn special attentions worldwide

and research work in this aspect has been carried out smoothly thanks to advanced CFD methods and high-precision wind tunnel test techniques. In this study

the cruise configuration of the civil aircraft model CAE-AVM (Chinese Aeronautical Establishment-Aerodynamic Validation Model) as wel

l as the overall layout and aerodynamic design of the baseline aircraft are introduced. The design characteristics of the long-range business aircraft and the aerodynamic standard model in this speed range are given

and special requirements and solutions for the wind tunnel test of the aerodynamic standard model are put forward. The CFD-experimental data correlation and the CAE-AVM database applications are also demonstrated. Results show that

under the condition of

= 0.85

lift coefficient

= 0.5 and Reynolds number 20 million

the estimated lift to drag ratio is 17.6

the buffet lift coefficient and the drag divergence Mach number all meet the design requirements. Simultaneous measurement of forces/moments

pressure distribution

wing aero-elastic deformation and transition front is achieved. Pre-test CFD analysis of the real test model with estimated wing deformation and model support greatly improves the efficiency of wind tunnel tests. The CAE-AVM database and its applications in CFD validation

CFD-test data correlation

modern wind tunnel test capacity development and civil aircraft design analysis demonstrate the theoretical and engineering values of the aerodynamic standard model in modern aircraft design.

关键词

Keywords

references

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