Journal of Applied Science and Engineering

Published by Tamkang University Press

1.30

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2.10

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Chang-Fei Zhuo This email address is being protected from spambots. You need JavaScript enabled to view it.1, Yan-Bing Zou1,2 and Peng Xu3

1School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, P.R. China
2Wuhan Guide Infrared Co., Ltd, Wuhan 430040, P.R. China
3The Technical Center of Jinxi Industries Group Co., Ltd, Taiyuan 030027, P.R. China


 

Received: March 29, 2017
Accepted: February 6, 2018
Publication Date: June 1, 2018

Download Citation: ||https://doi.org/10.6180/jase.201806_21(2).0008  

ABSTRACT


Numerical investigations of the supersonic flow over a base of cylinder using Reynolds averaged Navier-Stokes (RANS) method have been performed in detail in this paper. The flow is along a cylinder axis and separates suddenly at a blunt base corner. The performance of several turbulence models have been examined in this study. They include: Spalart-Allmaras(S-A), k-, k- BSL, and k- SST. Some important statistics computed for engineering in the wake region of the flow are compared with the experimental results for the same conditions and configurations. For k- SST turbulence model, the performance of three compressibility models are examined. In addition, the performance of numerical scheme for spatial discretization is examined for the supersonic base flow. In general, k- SST and k- BSL turbulence model perform better in the near wake than S-A and k- model, and predict the base pressure and axial length of the recirculation bubble much better. Three compressibility models for k- SST turbulence model perform much more different, and over-predict or under-predict the base pressure. From the numerical scheme point of view, AUSMPW+ scheme is more suitable for the numerical calculation of the base flow field about the supersonic flows.


Keywords: Computational Fluid Dynamics, Turbulence Model, Base Flow, Compressible Modification, Numerical Scheme


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