Computational Modeling of a Finned Projectile by Chimera Technique
ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
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A computational study was performed to compute the aerodynamic coefficients of a long-range finned projectile configuration at a transonic velocity of Mach 0.95 for multiple angles of attack. A zonal, implicit, Navier-Stokes computational technique, along with the Chimera overset grid approach, has been used to compute the projectile flow field. The application of the Chimera approach allowed for improved efficiency in terms of placing grid points where they are needed the most. This technique is promising for future flow field computations of finned projectiles. The aerodynamic coefficients computed are then compared with those computed through application of a design code to show comparable results.
- Fluid Mechanics