Computation of three-dimensional compressible flow from a rectangular nozzle with delta tabs

A three-dimensional viscous pow analysis is performed using a time-marching Reynolds-averaged Navier-Stokes code for a 3:1 rectangular nozzle with two delta tabs located at the nozzle exit plane to enhance mixing. Two flow co nfigurations, a subsonic jet case and a supersonic jet case using the same tab configuration, which were previously studied experimentally, are comput ed and compared with the experimental data. The experimental data include s treamwise velocity and vorticity distributions for the subsonic case, and M ach number distributions for the supersonic case, at various axial location s downstream of the nozzle exit. The computational results show very good a greement with the experimental data. In addition, the effect of compressibi lity on vorticity dynamics is examined by comparing the vorticity contours of the subsonic jet case with those of the the supersonic jet case which we re not measured in the experiment.