Numerical Study of Flow Over a Projectile

Abstract

Numerical study of flow over projectiles of circular arc profile with straight aftend is carried out by varying the nose angle and base radius. Four different cases of base radius with seven values of nose angle are taken for simulation at three different Mach numbers (1.2, 0.9, 0.5). 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 optimize the geometry of projectile. A comparative study of pressure drag coefficients in supersonic, transonic and subsonic regimes is presented here. Simultaneously variations of pressure, temperature and Mach number are analysed. It is observed that the optimum geometry at which pressure drag is minimum has nose angle between 6.225◦ to 5.274◦ at any value of base radius.