In the present study, the characteristics of a shock wave/vortex interaction for the enhancement of fuel air mixing in scramjet engines suitable for hypersonic vehicles is investigated. The scheme is based on the previous work developed by Kalkhoran et al. (1998) in the area of shock wave/vortex interaction in which a dramatic supersonic vortex bursting was shown. This study involves positioning a vortex generator, in the form of a semi-span wing section placed at an angle of attack, upstream of an injection slot. The vortex interacts with the naturally formed bow shock due to conventional injection, and for sufficiently strong interaction a supersonic vortex breakdown is expected. Computational investigations are conducted to validate the results of the experimental study using the Reynolds Stress Model (RSM). The results of the present computational investigation are in good agreement with the experimental data, confirming the characteristics of the supersonic vortex breakdown observed during the experimental study. Furthermore, computational results demonstrate the enhanced mixing and shortening of the combustion length for the cases involving the supersonic shock/vortex interaction.