全隐式E-CUSP迎风格式大攻角分离流数值模拟

郑秋亚 1; 2; 封建湖 1; 梁益华 3

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全隐式E-CUSP迎风格式大攻角分离流数值模拟

更新时间：2025-07-09

- 全隐式E-CUSP迎风格式大攻角分离流数值模拟
- Numerical Simulation of Separated Flows Around Slender Body at High-Angle-of-Attack By Fully Implicit E-CUSP Upwind Scheme
- 西安交通大学学报 2011年45卷第9期页码：54-58+113
- 作者机构：
  
  1. 长安大学理学院,西安,710064
  2. 西安电子科技大学理学院,西安,710071
- 作者简介：
- 基金信息：
  
  : 2011-01-28. 作者简介: 郑秋亚(1964-),女,博士生,高级工程师. 基金项目: 国家自然科学基金资助项目(60974082);航空科学基金资助项目(20081431)
- DOI：
  中图分类号： V211.3
- 网络首发：2011-09-10，
  
  纸质出版：2011
- 稿件说明：
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郑秋亚 1, 2, 封建湖 1, 等. 全隐式E-CUSP迎风格式大攻角分离流数值模拟[J]. 西安交通大学学报, 2011,45(9):54-58+113.

Numerical Simulation of Separated Flows Around Slender Body at High-Angle-of-Attack By Fully Implicit E-CUSP Upwind Scheme[J]. 2011, 45(9): 54-58+113.
郑秋亚 1, 2, 封建湖 1, 等. 全隐式E-CUSP迎风格式大攻角分离流数值模拟[J]. 西安交通大学学报, 2011,45(9):54-58+113. DOI：

Numerical Simulation of Separated Flows Around Slender Body at High-Angle-of-Attack By Fully Implicit E-CUSP Upwind Scheme[J]. 2011, 45(9): 54-58+113. DOI：

摘要

采用全隐式、低耗散E-CUSP格式

通过求解雷诺平均Navier-Stokes方程耦合Spalart-Allmaras(SA)湍流模型

模拟了细长旋成体在超声速、大攻角下的流场

分析了背风面涡的发展过程.结果表明:E-CUSP格式耦合SA湍流模型能够准确地模拟背风面的流动分离和精细的二次涡

对横向分离具有较高的模拟精度; 预测的物面压力系数分布和激波位置与实验数据吻合良好

力和力矩的相对误差在1.98%之内; E-CUSP格式可用于模拟复杂的分离流动

具有高的计算精度和效率.

Abstract

Adopting a fully implicit low diffusion E-CUSP(LDE)upwind scheme

the turbulent flow fields around a slender body at supersonic and high-angle-of-attack is numerically simulated by solving Reynolds averaged Navier-Stokes equations coupled with Spalart-Allmaras turbulence model. The leeward vortices developing process is analyzed. The results show that LDE scheme with the Spalart-Allmaras turbulence model enables to simulate leeward flow separation and capture the subtle secondary vortices with high accuracy

and has high simulation precision for cross separation. The predicted pressure distributions on the wall and shock wave positions coincide well with the experiment

and the relative errors of the obtained forces and moments are within 1.98% compared with the experimental data

which demonstrates that LDE scheme can be used to simulate complex separated flows with high accuracy and efficiency.

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Keywords

references

杨永,段毅,张强.超声速大攻角分离流中三种湍流模型的比较研究[J].空气动力学学报, 2006, 24(3): 371-375.

YANG Yong, DUAN Yi, ZHANG Qiang. Comparison of three turbulence models in supersonic high-attack-angle separated flows[J]. Acta Aerodynamica Sinica, 2006, 24(3): 371-375.

ESWAR J. Computational simulation improvements of supersonic high-attack-angle missile flows [J]. Journal of Spacecraft and Rockets, 1999, 36(1): 59-66.

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郑秋亚,刘三阳,周天孝.DLR-F6翼身组合体跨声速阻力计算[J]. 西安交通大学学报, 2010, 44(9): 115-121.

ZHENG Qiuya, LIU Sanyang, ZHOU Tianxiao. Transonic drag computation around DLR-F6 wing-body configurations [J]. Journal of Xi'an Jiaotong University, 2010, 44(9): 115-121.

ZHA Gecheng, HU Zongjun. Calculation of transonic internal flows using an efficient high resolution upwind scheme, AIAA 2004-1097 [R]. Reston, VA, USA: AIAA, 2004.

ZHA Gecheng, SHEN Yiqing, WANG Baoyuan. Calculation of transonic flows using WENO method with a low diffusion E-CUSP upwind scheme, AIAA 2008-0745 [R]. Reston, VA, USA: AIAA, 2008.

SPALART P R, ALLMARAS S R. A one-equation turbulence model for aerodynamic flows, AIAA Paper 92-0439 [R]. Reston, VA, USA: AIAA, 1992.

VAN LEER B. Towards the ultimate conservative difference scheme: Ⅴ A second-order sequel to Godunov's method [J]. Journal of Computational Physics, 1979, 32(1): 101-136.

WALTER B S, TREVOR B, MARC L, et al. The application of CFD to the prediction of missile body vertices, AIAA Paper 97-0637 [R]. Reston, VA, USA: AIAA, 1997.

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