The surface reflective visualization (SRV) system is used to investigate the vortical flowfield above a 65-deg sweep, sharp leading-edge, noncambered delta wing in a high subsonic flow. Configurations of M oo -α are considered that both do and do not exhibit vortex breakdown above the wing, with and without the presence of a terminating shock-wave system above the wing. The SRV system provides a new opportunity to investigate the behavior of vortex breakdown in the high subsonic regime as well as the spanwise distribution of the terminating shock-wave system above the wing. Two classes of vortex breakdown, asymmetric and symmetric, are observed.