Flow Visualization Measurement Techniques for High-Speed Transition Research in the Boeing/AFOSR Mach-6 Quiet Tunnel

Flow visualization experimental methods are developed for hypersonic boundary-layer instability and transition research. The techniques are applied to a scramjet forebody geometry in Purdue’s Boeing/AFOSR Mach-6 Tunnel. Fluorescent oil-flow visualization techniques are used to complement the instability measurements obtained with temperaturesensitive-paints. Gross flow features such as separated flow regions can be detected and quantified. Temperature-sensitive-paint is used to measure the surface temperature distribution, and the boundary layer instability due to streamwise vortices is inferred from the computed heat-transfer rates. The mean heattransfer rates are about a factor of ten larger than published 2-D laminar CFD data on the Hyper-X. Two major problems with the TSP technique applied in this facility are identified. The variation of the insulating layer thickness and the pressure sensitivity of the TSP introduce significant uncertainties. Despite these error sources, the small variations in the heat-transfer rate caused by the stationary instability, and its growth along the model are measurable.

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