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.