Computational Fluid DynamicsNo Access

A DDES study of the flow past a prolate spheroid using a high-order U-MUSCL scheme

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, 29 Yudao Street, Nanjing 210016, Jiangsu, P. R. China

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Zhen-Ming Wang

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, 29 Yudao Street, Nanjing 210016, Jiangsu, P. R. China

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Ning Zhao

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, 29 Yudao Street, Nanjing 210016, Jiangsu, P. R. China

E-mail Address: zhaoam@nuaa.edu.cn

Corresponding author.

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https://doi.org/10.1142/S0217979220400755Cited by:0 (Source: Crossref)

This article is part of the issue:

Special Issue — Proceedings of the Eighth International Symposium on Physics of Fluids (ISPF8), 10–13 June, 2019, Xi'an, China

Abstract

Flow past a prolate spheroid, which is a representative simplified configuration for vehicles such as maneuvering ships, submarines and missiles, comprises a series of complex flow phenomena including pressure-induced flow separation, which results in unsteady forces and movements that may be detrimental to vehicles’ performance. In this paper, a Delayed Detached Eddy Simulation (DDES) method combined with a new high-order U-MUSCL scheme is proposed to more precisely and accurately capture the flow separation and vortex structure. This method is applied to simulate the aerodynamic performance of the 6:1 prolate spheroid at an AOA of $2 0^{\circ}$ with the Reynolds number of $4.2 \times 1 0^{6}$ . Axial pressure distribution of five individual chord wise sections and flow field structure of the aft body are analyzed. Numerical results agree well with the experimental data. It can be concluded that DDES combined with three-order U-MUSCL scheme demonstrates reliable performance since it captures the vortex structure of aft body distinctly and predicts the separation and reattachment points of the secondary vortex precisely.

Keywords:

PACS: 47.27.Eq

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