Open AccessNumerical Investigation of the Aerodynamic Characteristics of a Missile
Author(s) -
Yu-shan Meng,
Li Yan,
Wei Huang,
Xin-yu Tong
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/887/1/012001
Subject(s) - mach number , missile , aerodynamics , aerospace engineering , supersonic speed , drag coefficient , computational fluid dynamics , head (geology) , mechanics , flow (mathematics) , solver , conical surface , fluent , engineering , drag , structural engineering , physics , mechanical engineering , computer science , geology , geomorphology , programming language
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.