The process of transition in three-dimensional hypersonic boundary layers is highly complex. For a cone at angle of attack, first mode, second mode, and crossflow instabilities are commonly present and can contribute to laminar breakdown. Based on recent experiments conducted in the Purdue Boeing/AFOSR Mach 6 quiet tunnel, two direct numerical simulations of a 7.0° half angle sharp cone in Mach 6 flow at an angle of attack of 6.0° were completed in order gain further insight into the transition process. These simulations were generated on appropriately resolved grids using a high-order, low-dissipation scheme that has been developed at the University of Minnesota and incorporated into the computational fluid dynamics solver US3D. Comparisons of the experimental observations were made with the direct numerical simulations.