Transition from laminar to turbulent hypersonic boundary layers is the topic of several research projects world-wide. Most experimental work is done in conventional wind tunnels, although their free stream turbulence does not match free flight conditions and has a significant in§uence onto the transition process. Experiments performed with the same 3 degree half angle cone in a conventional and a quiet wind tunnel at Mach 6 justify this approach. The formation, amplification, and decay of the second (Mack) modes is compared based on high-frequency pressure measurements. In addition, damping of these modes with ultrasonically absorptive surfaces was tested.
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Willems et al. (2017) studied this question.
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