A computational code has been developed to predict the flowfield about supersonic flow over an axisymmetric conical afterbody containing a centered propulsive jet with and without the recirculatory base flow region. The compressible, Reynolds-average, full Navier-Stokes equations are solved using a time-dependent, implicit numerical algorithm of Beam and Warming. Baldwin-Lomax model is used to provide turbulent closure. The developed code has been found to mimic the complex supersonic base flow features. The predicted results are compared, when possible, with the experimental data.
