Direct Numerical Simulation is being used to study crossflow instabilities on the Hypersonic International Flight Research Experimentation program flight 5 vehicle. The simulations replicate a 38.1% scale model at the 1090 kPa flight conditions used for experiments at the Boeing/AFOSR Mach 6 Quiet Tunnel. In this paper special attention is given to the development of a baseflow for the problem. Due to the extreme sensitivity of crossflow instability, disturbances are seeded very easily and can pollute the baseflow. Several computations designed to limit this phenomenon while still resolving the mean flow physics are presented. A simulation of a quarter of the HIFiRE-5 forebody with 216 million elements is being performed. Once completed, the development and breakdown of crossflow vortices will be analyzed, with attention given to spanwise wavenumber evolution, nonlinear interaction and modification of the mean flow, and the fostering of secondary instabilities.
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