Computational aerodynamic study of a supersonic reference projectile

Abstract

In the present paper results of computational aerodynamic study of a reference projectile in supersonic flow is presented. Pressure distribution along the projectiles nose in longitudinal and circumferential direction was studied using numerical simulations. Static aerodynamic coefficients in the freestream Mach numbers of 3 and 4 at an angle of incidence of -4 to 20 degrees were computed. For validation, the numerical solution was initially compared for the conic part with the experimental results and found to be in good agreement. Nose related aerodynamic features were initially studied in the first part of the study. Further complete projectile’s aerodynamic analysis is carried out. The present paper covers the results obtained in the study conducted for the projectile’s geometry. Significant flow features were investigated, including correct capturing of bow shock’s location, low pressure density/pressure variations in the low pressure regions along with its influence on the stagnation zone. Further evaluation of peak pressure values associated with the stagnation region on the nose was made. Also, static aerodynamic coefficients were computed to depict projectile’s static stability.