Applicability investigation about several common schemes and turbulence models in high speed flow

SHI Lei; YAN Ming; YANG Yun-jun; ZHOU Wei-jiang

doi:10.13224/j.cnki.jasp.2014.08.019

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Applicability investigation about several common schemes and turbulence models in high speed flow

更新时间：2026-07-07

- Applicability investigation about several common schemes and turbulence models in high speed flow
- Issue 8, (2014)
- 作者机构：
  
  中国航天科技集团公司中国航天空气动力技术研究院,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.08.019
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
石磊, 闫溟, 杨云军, 周伟江. 几种常用格式和湍流模型在高速流动中的适用性研究[J]. 航空动力学报, 2014, (8): 1904-1910. doi: 10.13224/j.cnki.jasp.2014.08.019

SHI Lei, YAN Ming, YANG Yun-jun, et al. Applicability investigation about several common schemes and turbulence models in high speed flow[J]. 2014, (8).
石磊, 闫溟, 杨云军, 周伟江. 几种常用格式和湍流模型在高速流动中的适用性研究[J]. 航空动力学报, 2014, (8): 1904-1910. doi: 10.13224/j.cnki.jasp.2014.08.019 DOI：

SHI Lei, YAN Ming, YANG Yun-jun, et al. Applicability investigation about several common schemes and turbulence models in high speed flow[J]. 2014, (8). DOI： 10.13224/j.cnki.jasp.2014.08.019.

摘要

针对高超声速飞行器中存在的强激波、激波/边界层干扰、分离、湍流等复杂流动现象，对比分析了当前计算流体力学中的主要空间离散格式及湍流模型，发现不同格式对强激波的分辨率基本相同，Roe和LDE（low diffusion E-CUSP（convective upwind split pressure））格式对摩擦因数和传热系数的模拟优于其他格式；S-A（Spalart-Allmaras）一方程湍流模型计算的摩擦因数比k-ω SST（shear stress transport）两方程湍流模型高10%左右，而后者预测的分离区约为前者的2倍，且分离点靠前.

Abstract

Several common spatial dispersion schemes and turbulence models in current computational fluid dynamics were compared and analyzed to investigate complex flow phenomenons such as strong shock waves

shock waves/boundary layer interaction

flow separation and turbulent flow in hypersonic flight. The results demonstrate that the resolutions of strong shock waves are the same by different schemes. Roe and LDE (low diffusion E-CUSP (convective upwind split pressure)) schemes show better agreement in friction coefficient and heat transfer coefficient with experimental data than other schemes. The friction coefficient predicted by S-A (Spalart-Allmaras) turbulence model is greater than that by k-ω SST (shear stress transport) turbulence model about 10%. The separation zone of the latter is twice the size of the former and the separation point is located in front.

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Related Institution

School of Aeronautics and Astronautics, Zhejiang University

中国航天科技集团有限公司中国航天空气动力技术研究院

清华大学航天航空学院

中国航空工业集团有限公司沈阳飞机设计研究所

北京航空航天大学航空科学与工程学院

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