Three Dimensional Transonic Flow Computations Over a Projectile and at the Base Region

A three dimensional base flou. code has been developed to predict the flow field around projectiles, including forebody and afterbody flows at transonic speeds. full navier-stokes equations are solved using finite volume and runge-kutta time stepping techniques to compute the full flow field around a projectile including the base region at angle of attack. flow field solutions have been obtained for a typical artillery projectile at mach number, m=0.96 and 4 degree angle of attack. details of the flow field on the boat-tailed after body and in the base region are presented. surface pressure, base pressure and aerodynamic coefficients are computed and compared with experiments and the sahu's computational results are achieved using thin layer approximation of governing equations.