高精度IPDG湍流模拟及通量格式数值特性

郝世熙; 丁秋实; 魏桐; 刘正先; 刘伟; 李孝检; 赵明

doi:10.7638/kqdlxxb-2022.0149

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高精度IPDG湍流模拟及通量格式数值特性

研究论文 | 更新时间：2026-05-28

- 高精度IPDG湍流模拟及通量格式数值特性
- High-precision IPDG based turbulence simulation and the numerical characteristics of flux schemes
- 空气动力学学报 2023年41卷第11期页码：94-102
- 作者机构：
  
  1. 天津大学机械工程学院,天津,300350
  2. 电子科技大学计算机科学与工程学院,成都,611731
- 作者简介：
  
  郝世熙（1997-），男，河南人，研究方向：CFD高精度数值方法. E-mail：haoshixicup@126.com
  赵明*，副教授，研究方向：计算流体力学数值方法、流动控制方法、涡动力学. E-mail：ming.zhao@tju.edu.cn
- 基金信息：
  
  国家自然科学基金（11972250，12102298）;天津市自然科学基金（20JCQNJC01950）
- DOI：10.7638/kqdlxxb-2022.0149
  中图分类号： O354
- 纸质出版：2023
- 稿件说明：
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郝世熙, 丁秋实, 魏桐, 等. 高精度IPDG湍流模拟及通量格式数值特性[J]. 空气动力学学报, 2023, 41(11): 94−102.

HAO Shixi, DING Qiushi, WEI Tong, et al. High-precision IPDG based turbulence simulation and the numerical characteristics of flux schemes[J]. 2023, 41(11): 94-102.
郝世熙, 丁秋实, 魏桐, 等. 高精度IPDG湍流模拟及通量格式数值特性[J]. 空气动力学学报, 2023, 41(11): 94−102. DOI： 10.7638/kqdlxxb-2022.0149

HAO Shixi, DING Qiushi, WEI Tong, et al. High-precision IPDG based turbulence simulation and the numerical characteristics of flux schemes[J]. 2023, 41(11): 94-102. DOI： 10.7638/kqdlxxb-2022.0149.

摘要

为更高精度数值求解复杂湍流问题，在内罚间断伽辽金（internal penalty discontinuous Galerkin

IPDG）方法框架内发展了基于SST

k-ω

模型的湍流模拟方法，通过对亚/跨/超声速工况下流场的数值计算与湍流特征捕捉，验证了方法的适用性，进而系统分析了AUSM、Lax-F、HLL和Roe 4种通量格式在IPDG湍流模拟中的数值特性。结果表明：AUSM格式在超声速工况下脱体激波面“褶皱”现象明显；Lax-F格式和HLL格式数值耗散大，在激波解析方面精度较低，且Lax-F格式在激波脚后诱导产生流动分离；Roe格式具备宽速域适用性，计算精度较高且能精确解析激波结构。

Abstract

In this study

the SST

k-ω

turbulence model is applied within the framework of the internal penalty discontinuous Galerkin (IPDG) method. The applicability of the method is verified by numerical simulations of the flow fields and the turbulence characteristics under subsonic

transonic and supersonic conditions. Based on the present method

the numerical characteristics of four different flux schemes (AUSM

Lax F

HLL and Roe) for the convection term in the weak form of the RANS equations with IPDG are systematically analyzed. The results show that

the AUSM scheme presents an obvious folding phenomenon on the detached shock surface under supersonic condition. The Lax-F and HLL scheme

s have large numerical dissipation and perform poorly in the shock wave analysis. Moreover

flow separation is induced after the shock surface in the Lax-F scheme. The Roe scheme has the applicability for a wide range of velocity

and presents a high calculation accuracy that can precisely resolve the shock structure.

关键词

Keywords

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