Evolution of vortex structures on the leeward side of a delta wing

Results of an experimental study of a supersonic flow around the leeward side of a delta wing are presented. The experiments are performed on three delta wings with leading–edge sweep angles $\chi = 68^\circ$, $73^\circ$, and $78^\circ$ for Mach numbers $\mathrm{M} =2-4$ and angles of attack $\alpha=0-22^\circ$. Data on the structure and position of internal shock waves are obtained; the size and location of primary and secondary vortices are found. New regimes of the flow around a delta wing are identified. The chart of flow regimes around delta wings is refined and extended.