Numerical simulation of the standard model CHN-T1 based on overset grid

DU Yiming; PANG Chao; SHU Bowen; GAO Zhenghong

doi:10.7638/kqdlxxb-2018.0195

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Numerical simulation of the standard model CHN-T1 based on overset grid

更新时间：2026-05-28

- Numerical simulation of the standard model CHN-T1 based on overset grid
- Vol. 37, Issue 2, Pages: 280-290(2019)
- 作者机构：
  
  西北工业大学航空学院翼型叶栅空气动力学重点实验室,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0195
  CLC： V211.3
- Published：2019
- 稿件说明：
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杜一鸣, 庞超, 舒博文, 高正红. 基于嵌套网格的CHN-T1标模数值模拟[J]. 空气动力学学报, 2019, 37(2): 280-290.

DU Yiming, PANG Chao, SHU Bowen, et al. Numerical simulation of the standard model CHN-T1 based on overset grid[J]. 2019, 37(2): 280-290.
杜一鸣, 庞超, 舒博文, 高正红. 基于嵌套网格的CHN-T1标模数值模拟[J]. 空气动力学学报, 2019, 37(2): 280-290. DOI： 10.7638/kqdlxxb-2018.0195.

DU Yiming, PANG Chao, SHU Bowen, et al. Numerical simulation of the standard model CHN-T1 based on overset grid[J]. 2019, 37(2): 280-290. DOI： 10.7638/kqdlxxb-2018.0195.

摘要

为响应第一届航空CFD可信度研讨会（AeCW-1），对CHN-T1标模翼身-尾翼组合体构型采用两种RANS求解器进行了基于结构化嵌套网格的网格收敛性研究和抖振特性计算，并与对接网格结果进行了对比分析。参考AeCW-1网格生成指南自主研发了一族以约3.3倍规模增长的稀-中等-密-特密嵌套网格系列。相比于分区点对接网格，融合了贴体网格和笛卡尔网格优势的嵌套网格从根本上降低了网格生成难度，单块网格拓扑形式更为合理且正交性较好，同时能够有效地平衡近场和远场的网格量。对于跨音速运输机构型，同等规模下嵌套网格的物面网格密度较对接网格更大，能够对激波和分离等复杂流动进行更理想的预测。对比计算过程中，自研求解器OFS3D表现出了较高的嵌套网格计算效率和可靠性，而NASA CFL3D求解器的嵌套网格计算能力有待进一步挖掘和验证。计算还发现，不同湍流模型得到的表面压力分布、分离区大小以及最大升力系数存在差别，而风洞模型支撑和机翼静气弹变形对飞行器力矩特性预测影响较大。

Abstract

In response to the 1st Aeronautics CFD Credibility Workshop

the CARDC CHN-T1 wing-body-tail configuration was analysed by two RANS solvers. A family of structured overset grids with equivalent parameters were generated. In these grids

four levels of grid size were used

and the number of grid cells from one level to the next refined level was increased by a factor of roughly 3.3. Based on these grids

studies were conducted regarding grid-convergence study and buffet prediction. Moreover

the results were compared with those from 1-1-blocking grid. The overset grid integrates the advantages of body-fitted grid and Cartesian grid. These advantages lead to radically reducing the generation complexity with compact blocking topology and superior near-field orthogonality. For the numerical simulation of transonic transport airplanes

overset grids have high resolution for shock waves and flow separations since more cells can be assembled on the wall compared with that of 1-1-blocking grids with the same mesh scale. The in-house code adopted in the present work possesses satisfactory computation efficiency and reliability

while the ability of NASA CFL3D solver in respect of overset grid needs further excavation and verification. The displayed results also include the difference between SA and SST turbulence model on predicted surface pressure distribution

separation bubbles and maximum lift coefficient. It is revealed that the model support in wind tunnel and the static aeroelastic deformation of the wing have great influence on the pitching moment of the model airplane.

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references

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