Development of Hypersonic Quiet Tunnels

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Developing mechanism-based methods for estimating hypersonic boundary-layer transition in flight: The role of quiet tunnels (2013, methodology): “However, these quiet noise levels require laminar nozzle-wall boundary layers, and are presently available only in three wind tunnels at Mach 6 and moderate Reynolds numbers, in cold flow [41, 43, 44].”
Effects of Roughness on Hypersonic Boundary-Layer Transition (2007, unknown): “For these quiet-nozzle designs, the thin boundary layer makes the transonic throat the most sensitive area, and this Rek ’ 12 criteria has proved useful, although it is subject to much uncer tainty [39].”