A Numerical Study of Flow Over A Projectile

Abstract

Numerical study of flow over a projectile of circular arc profile with straight aft end is carried out by varying the nose angle and base radius for a supersonic case. Four different cases of base radius with seven values of nose angles are taken for simulation. Two dimensional axisymmetric Euler equations are solved using pressure correction technique to get the converged solution. The results show the effect of curvature of projectile profile on the aerodynamic characteristics and various flow field parameters. Drag is taken as the vital parameter to optimise the geometry of projectile. It is observed that the optimum geometry at which drag is minimum has nose angle between 6.225◦ to 5.274◦ irrespective of the base radius.