A computational model is developed using a delayed detached-eddy simulation to examine the various aspects of shock-wave/vortex interactions, in which the specific case of naturally formed bow shock wave generated during a sonic injection into a supersonic crossflow is considered. The model is validated by comparing with experimental results obtained previously and is deployed to investigate the effects of shock/vortex interaction on mixing characteristics of supersonic flows. A vortex generator, in the form of a semispan wing section, is placed at an angle of attack upstream of an injection location. The resultant vortex interacts with the bow shock, and for a sufficiently strong interaction, there is breakdown of the supersonic vortex. The vortex bursting observed during the computational study is in a very good agreement with a previous physical model. The computational results demonstrate that the shock/vortex interaction can be an effective method of mixing enhancement because it results in redistribution and increase of vorticity in the flowfield, which enhances the entrainment and eventual mixing of injectant and supersonic crossflow.
ASJC Scopus subject areas
- Aerospace Engineering