Abstract
The unsteady compressible flow around a 50 mm projectile governed by the Navier-Stocks (NS) equation is numerically solved with a Large Eddy Simulation (LES) method, with the Sub-Grid Scale (SGS) solved by Smagorinsky-Lilly model. The computed results are obtained in supersonic flow regime for a viscous fluid in order to determine the aerodynamic coefficients with different angles of attack. The flow around a body tail projectile was solved as a three-dimensional flow.
Highlights
The flow around a projectile presents turbulent boundary layers, whose separation is a usual phenomena and a large turbulent wake formed at the bottom of the object
The objective of the present study is to provide a methodology for the determination of the aerodynamic coefficients of a projectile of given geometry using the more recent advances in computational fluid dynamic technique
The Computational Fluid Dynamics (CFD) is applied to determine the aerodynamic coefficients by using a commercial CFD code called FLUENT which solves the governing equations of the flow motion using a technique of finite volume
Summary
The flow around a projectile presents turbulent boundary layers, whose separation is a usual phenomena and a large turbulent wake formed at the bottom of the object. Prevention or control of the separation of the boundary layer is one of the most important aims, as well as an appropriate ogive design [1] [2] As it is well known, a turbulent flow carries irregular and fluctuating fluid motions which contribute significantly to the transport phenomena. Wessam et al tions of the flow motion using a technique of finite volume and takes the meshed computational domain from a pre-processor program called ICEM-CFD in which the model of the projectile is drawn and the computational domain is generated and meshed into cells. The full scale 50 mm projectile with a tapered leading and trailing fin edge and sharp nose tip was modeled in the CFD simulations Figure 1 [7], in order to determine the aerodynamic coefficients. The fin trailing edge was flush with the projectile base
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