Understanding the aerothermodynamics of gliding hypersonic vehicles is of interest to the Depat1ment of Defense. The goal of this work was to study the aerothermodynamics associated with the generic model of a straight slender cone with a highly swept fin (Chynoweth et al. 2014), featuring highly-swept-shock/boundary-layer interactions and corner flows associated with the intersection of the fin and the body. Laminar-to-turbulent transition under these conditions affects heat transfer and boundary-layer separation. Expected were various modes to include Mack's second mode, corner-flow instabilities, crossflow, and so forth, coupled with oblique shocks. The primary focus of this three-year effort was on understanding and modeling of the transition and heating process. Due to the fact that transition is highly sensitive to even small effects, careful verification and validation were key to this research, and interactions with Professor Steven Schneider's experimental group at Purdue were integral to this work.