Abstract
The process via which a hypersonic boundary layer transitions from laminar to turbulent flow is important in determining the length of transitional flow regions which is important information for designers of hypersonic vehicles. The effects of bluntness of the leading edge of the hypersonic body on the unsteady processes in the transitional region have not received much attention in the literature. This paper compares the unsteady processes in the transitional region for a slender cone with both a sharp and a blunted tip at hypersonic flow conditions in the T4 Stalker Tube. Fewer, more isolated turbulent spots were observed for the blunted than for the sharp cone when tested at similar or higher Reynolds number conditions.
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Mee, D.J., Raghunath, S. (2019). Boundary Layer Transition Measurements on Sharp and Blunt Cones in the T4 Stalker Tube. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 2. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91017-8_142
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DOI: https://doi.org/10.1007/978-3-319-91017-8_142
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