The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.