Numerical Investigation of the Aerodynamic Characteristics of a Missile

During supersonic flight of supersonic missile, the missile configuration has great influence on the aerodynamic characteristics of the missile. This article evaluates the variation of the flow field results from the change of missile configuration by changing the shape of the head and the slenderne...

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Bibliographic Details
Published in:IOP conference series. Materials Science and Engineering 2020-07, Vol.887 (1), p.12001
Main Authors: Meng, Yu-shan, Yan, Li, Huang, Wei, Tong, Xin-yu
Format: Article
Language:English
Subjects:
Aerodynamic characteristics
Aerodynamics
Computational fluid dynamics
Drag coefficient
Drag coefficients
Flow simulation
Head shape
Mach number
Mathematical analysis
Mathematical models
Missile configurations
Numerical analysis
Numerical methods
Slenderness ratio
Stagnation temperature
Structured grids (mathematics)
Supersonic flight
Supersonic missile
Three dimensional flow
Three dimensional models
Two dimensional models
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Summary:During supersonic flight of supersonic missile, the missile configuration has great influence on the aerodynamic characteristics of the missile. This article evaluates the variation of the flow field results from the change of missile configuration by changing the shape of the head and the slenderness ratio of the body. The study is carried out by the CFD numerical method, and the structured grids are generated by ANSYS CFD software. We evaluate the aerodynamic characteristics of two-dimensional model and three-dimensional model by the flow solver FLUENT, and the standard Spalart-Allmaras one-equation is selected to simulate the flow around the missile, the results indicate that the drag coefficient of the oval head is less than parabolic head case and conical head case, and drag coefficient decreases with the increase of Mach number and slenderness ratio. With the increase of Mach number, the stagnation temperature increases correspondingly.
ISSN:1757-8981
1757-899X
DOI:10.1088/1757-899X/887/1/012001