A Preliminary Numerical Assessment of the 155 mm Projectile

This study conducts a computational analysis of aerodynamic coefficients for a 155 mm artillery projectile M107 at subsonic and supersonic speeds, focusing on the impact of varying tail angles. The research uses ANSYS FLUENT to treat the flow, capturing crucial phenomena like shock waves. Key findings include significant effects of tail angle variations on drag and lift coefficients, essential for projectile design optimization. The study validates the simulation results against experimental data, proving the model's accuracy and the critical role of tail design in aerodynamic control. It offers insights for military and aerospace applications.