This paper describes a computational and experimental study of the flow field in a supersonic nozzle flow including the effects of fluidic inserts. Fluidic inserts involve carefully directed blowing in the diverging section of a convergent divergent nozzle. This blowing changes the effective area ratio of the nozzle and also generates streamwise vorticity. As in the case of corrugated seal inserts, these modifications to the jet flow reduce the broadband shock-associated noise and also reduce the noise in the peak noise radiation direction. The focus of the present paper is on the flow field generated by the fluidic inserts rather than the changes in the radiated noise, which are reported elsewhere. Reynolds-Averaged Navier-Stokes simulations using a two-equation turbulence model are performed. The simulations are compared with flow measurements with a Laser Doppler Velocimeter. Flow predictions are made for a nozzle with three fluidic inserts, each generated by two injectors. An overexpanded jet operating condition is considered with and without core flow heating. The effects of different injector pressure ratios are examined. The distributions of Mach number, turbulent kinetic energy, total temperature, and streamwise vorticity are used to describe the features of the fluidic inserts. Though there are strong similarities between the effect on the core flow of the fluidic inserts and hard-walled corrugated seals, some interesting differences are identified. For example, the streamwise vortices in the hard-walled case are found in the corners of the corrugations, whereas for the fluidic inserts the vortices are confined to the interior of the corrugation.