Numerical Investigation of the Aerodynamic Characteristics of a Missile

• 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
• ISSN: 1757-8981; 1757-899X
• DOI: 10.1088/1757-899X/887/1/012001

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.