Abstract
The paper describes a solving procedure of the special Finite Volume Method (FVM) problem dealing with calculation of a flow field around air-to-air missile at subsonic, transonic and supersonic velocity range in order to obtain a coefficient of drag (cD). Some emphasis is put on numerical solution and fundamentals of FVM and use of a k-ω turbulence model for simulation of subsonic and supersonic flow fieldsaround air-to-air missile AIM-9 Sidewinder version M. Obtained results of missile aerodynamics characteristics are verified using semi-empirical software and by analysis of flow fields.
Highlights
Computational Fluid Dynamics (CFD) is already a classical branch of a contemporary fluid dynamics
This paper will describe the procedure for solving the special Finite Volume Method (FVM) problem which deals with calculation of flow field around air-to-air missile at subsonic, transonic and supersonic speed range in order to obtain Coefficient of Drag. coefficient of drag (cD) is the most required aerodynamic coefficient, which is required in missile performance calculations
There are no loosely available aerodynamic characteristics dealing with air-to-air missile bodies, which we can compare because of worldwide restrictions in defense industry
Summary
Computational Fluid Dynamics (CFD) is already a classical branch of a contemporary fluid dynamics. In the past few decades, the CFD used personal computers or work stations with appropriate software based on data structures and numerical analysis to solve problems involving interaction between fluid and solid object in defined integration domain. The growing importance of FVM reflects increased requirements for higher missile velocity, higher maneuver ability or other tactical demands. Another factor in rising role of FVM is improved engineering effectivity in scope of design and development processes of missiles systems, as well as their analysis. This paper will describe the procedure for solving the special FVM problem which deals with calculation of flow field around air-to-air missile at subsonic, transonic and supersonic speed range in order to obtain Coefficient of Drag (cD). The integration volume, in which the fluid medial will act on to surface of examined object
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