基于非结构混合网格的CHN-T1标模气动特性预测

张耀冰; 唐静; 陈江涛; 邓有奇

doi:10.7638/kqdlxxb-2018.0201

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基于非结构混合网格的CHN-T1标模气动特性预测

专栏——CFD验证与确认 | 更新时间：2026-05-28

- 基于非结构混合网格的CHN-T1标模气动特性预测
- Aerodynamic characteristics prediction of CHN-T1 standard model with unstructured grid
- 空气动力学学报 2019年37卷第2期页码：262-271
- 作者机构：
  
  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
- 作者简介：
  
  张耀冰(1980-), 男, 山西运城人, 博士, 主要从事亚跨超声速计算空气动力学研究.E-mail:zhyb_super@sina.cn
  陈江涛(1983-), 男, 山东莱州人, 硕士, 主要从事亚跨超声速计算空气动力学研究.E-mail:chenjt02@sina.cn
- 基金信息：
  
  国家重点研究发展计划（2016YFB0200700）
- DOI：10.7638/kqdlxxb-2018.0201
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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张耀冰, 唐静, 陈江涛, 邓有奇. 基于非结构混合网格的CHN-T1标模气动特性预测[J]. 空气动力学学报, 2019, 37(2): 262-271.

ZHANG Yaobing, TANG Jing, CHEN Jiangtao, et al. Aerodynamic characteristics prediction of CHN-T1 standard model with unstructured grid[J]. 2019, 37(2): 262-271.
张耀冰, 唐静, 陈江涛, 邓有奇. 基于非结构混合网格的CHN-T1标模气动特性预测[J]. 空气动力学学报, 2019, 37(2): 262-271. DOI： 10.7638/kqdlxxb-2018.0201.

ZHANG Yaobing, TANG Jing, CHEN Jiangtao, et al. Aerodynamic characteristics prediction of CHN-T1 standard model with unstructured grid[J]. 2019, 37(2): 262-271. DOI： 10.7638/kqdlxxb-2018.0201.

摘要

本文使用自行研制的基于非结构混合网格的亚跨超声速流场解算器MFlow，对AeCW-1提供的客机标模CHN-T1进行了数值模拟研究。介绍了非结构混合网格的生成情况，重点分析了网格收敛特性、压力分布、气动特性曲线、流动分离等。计算得到了近似线性的网格收敛特性。随着网格加密，对激波和分离气泡的模拟更精细。尾支撑对气动特性的影响非常明显，特别是对平尾气动特性有很大影响。机翼静气动弹性变形的影响主要是使升力系数和阻力系数减小。湍流模型的QCR修正对大迎角计算结果有较大的影响。计算结果表明，MFlow程序能够准确地预测客机标模的气动特性。

Abstract

The precise prediction of lift

drag and moments is one of the key factors in the aerodynamic design of transport aircraft. To assess computational methods as practical aerodynamic tools for aircraft force and moment prediction of industry relevant geometries

numerical investigations of the civil passenger aircraft model CHN-T1 supplied by the AeCW-1 workshop are performed with in-house flow field solver MFlow. The solver

based on a cell-centered finite-volume method

is capable of handling various element types (hexahedron

tetrahedron

prism

pyramid

and other polyhedrons generated when geometrical multi-grid method is used) and suitable for the simulation of subsonic

transonic and supersonic flows. The generation of unstructured mixed grid for CHN-T1 is introduced together with the gridding guidelines

and aerodynamic characteristics are analyzed

including grid convergence properties

pressure distribution

aerodynamic characteristic curve

and flow separation. A nearly linear convergence property is achieved with grid refinement

which implies that the solver is well established

and the solutions are within the asymptotic range. The resolutions for the shock and separation bubble are improved with the grid refinement. Several factors that contribute to the simulations are investigated

including the support system

the static aero-elasticity effects

and turbulence model corrections. It is found that the influence of the sting is significant

especially on the aerodynamic characteristic of the horizontal tail. Lift and drag coefficients are decreased due to the static aero-elasticity effects of the wing. The influence of the QCR correction for turbulence models is evident when the angle of attack is high. It is demonstrated that MFlow is capable of predicting the aerodynamics characteristics for aviation standard models.

关键词

Keywords

references

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