Hypersonic Wind-Tunnel Measurements of Boundary Layer Pressure Fluctuations.

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Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown (2015, methodology): “The stagnation temperature and pressure are 430 K and 1043 kPa, respectively (see Casper et al. 2009; Alba et al. 2010).”
Developing mechanism-based methods for estimating hypersonic boundary-layer transition in flight: The role of quiet tunnels (2013, background): “[61, 62] show that the breakdown amplitude increased with Mach number, from 5% at Mach 5 to 12% at Mach 6 and 24% at Mach 8.”