Numerical simulation of a jet interacting with a supersonic crossflow

The interaction of a jet and a supersonic crossflow has been simulated by solving Navier-Stokes equations using a dissipative difference scheme and with an NND scheme which is nonoscillatory and contains no free parameters. The results clearly depict the shock structure, recirculation regions, and mixing layer. The shock structure agrees well with experimental results. The most interesting characteristics of the calculated flow is the bifurcations of the primary vortex in front of the injector due to the interaction of the jet and the crossflow. Three streamwise rotating vortices and two counterrotating vortices can be observed. A wake flow with relatively lower pressure and a recirculation zone exist on the lee side of the injector.