Abstract
The leeward flow field of a sharp fin mounted above a flat plate generating a shock/turbulent boundary-layer interaction (STBLI) at Mach 2.5 was numerically studied. The fin had a 60 deg leading-edge sweep. Cases with and without a gap between the fin and the flat plate were investigated. In all cases, a vortex at the fin leading edge was generated due to the pressure difference across the fin leeward and windward sides. In the cases with gaps, an additional vortex is generated due to flow through the gap. The results agree well with those obtained from delta wing experiments. In contrast to full delta wing results, mounting the fin to the plate noticeably altered the lambda shock shape, but the vortex core location was relatively unchanged.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
