采用TRIP3.0模拟CHN-T1模型气动特性

李伟; 王运涛; 洪俊武; 孟德虹; 李桦

doi:10.7638/kqdlxxb-2018.0225

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采用TRIP3.0模拟CHN-T1模型气动特性

专栏——CFD验证与确认 | 更新时间：2026-05-28

- 采用TRIP3.0模拟CHN-T1模型气动特性
- Aerodynamic characteristics simulation of CHN-T1 model with TRIP3.0
- 空气动力学学报 2019年37卷第2期页码：272-279
- 作者机构：
  
  1. 国防科技大学空天科学学院,长沙,410073
  2. 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：
  
  李伟(1986-), 男, 四川梓潼人, 硕士, 助理研究员, 研究方向:计算空气动力学.E-mail:liwei_kd@163.com
  洪俊武, 研究方向:计算空气动力学.E-mail:hjw128@sina.com
- 基金信息：
  
  国家重点研究发展计划（2016YFB0200700）
- DOI：10.7638/kqdlxxb-2018.0225
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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李伟, 王运涛, 洪俊武, 孟德虹, 李桦. 采用TRIP3.0模拟CHN-T1模型气动特性[J]. 空气动力学学报, 2019, 37(2): 272-279.

LI Wei, WANG Yuntao, HONG Junwu, et al. Aerodynamic characteristics simulation of CHN-T1 model with TRIP3.0[J]. 2019, 37(2): 272-279.
李伟, 王运涛, 洪俊武, 孟德虹, 李桦. 采用TRIP3.0模拟CHN-T1模型气动特性[J]. 空气动力学学报, 2019, 37(2): 272-279. DOI： 10.7638/kqdlxxb-2018.0225.

LI Wei, WANG Yuntao, HONG Junwu, et al. Aerodynamic characteristics simulation of CHN-T1 model with TRIP3.0[J]. 2019, 37(2): 272-279. DOI： 10.7638/kqdlxxb-2018.0225.

摘要

采用TRIP3.0软件平台（TRIsonic Platform version 3.0），对第一届航空CFD（Computational Fluid Dynamics）可信度研讨会组委会提供的运输机标模构型（CHiNa-Transport，CHN-T1）进行了流动数值模拟。本文采用粗、中、细三套网格及百亿极细网格进行了网格收敛性研究；采用相应网格分别从气动特性、压力系数分布曲线、表面流态三个方面分析，研究了支撑装置、机翼静弹性变形以及雷诺数效应对CHN-T1构型气动特性的影响。数值模拟结果与试验结果有良好的一致性。数值模拟得到了网格收敛结果；支撑装置对力矩特性影响较大；机翼静弹性变形对气动特性影响较小；雷诺数效应对气动力特性影响较大。

Abstract

Based on the TRIsonic Platform Version 3.0 (TRIP3.0) software

the flow over CHiNa-Transport (CHN-T1) configuration supplied by the committee of 1st Aeronautic CFD Credibility Workshop

is simulated. The grid convergence is studied by the coarse

medium

fine meshes and the extremely fine one with ten billion grid points. The influence of the tail support

static aeroelasticity of the wing and the Reynolds number effect on the aerodynamic characteristics is investigated by suitable grids. Aerodynamic force coefficient

pressure distributions

and flow patterns on the surface are analyzed. The numerical results agree well with the experimental data. Grid refinement leads to convergence numerical results. It is demonstrated that the tail support has dramatic influence on the moment. The static aeroelasticity of the wing has little influence on the aerodynamic characteristics and Reynolds number effect has obvious influence on the aerodynamic force coefficient.

关键词

Keywords

references

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