Numerical computation of base flow for a missile in the presence of a centered jet

Abstract

Abstract : A thin-layer Navier-Stokes base flow code, developed for projectile aerodynamics, has been used to compute the missile base flow in the presence of a centered propulsive jet. The thin-layer, compressible, Navier-Stokes equations are solved using a time dependent, implicit numerical algorithm. Numerical computations have been made to predict the missile afterbody flow field for both jet-off and jet-on conditions. Solutions are obtained for an axisymmetric cylindrical afterbody where the free stream Mach number is 1.343 and the jet exit Mach number is 2.7. The exhaust jet static pressure is 2.15 times the free stream static pressure. Computed results show both qualitative and quantitative features of the base region flow field.