TY - JOUR
T1 - Hypersonic transitional shock-wave–boundary-layer interaction on a flat plate
AU - Currao, Gaetano M.D.
AU - Choudhury, Rishabh
AU - Gai, Sudhir L.
AU - Neely, Andrew J.
AU - Buttsworth, David R.
N1 - Funding Information:
The authors are in large debt to Chris Kennell, who manufactured most of the wind tunnel models and provided technical guidance during the design phase. Numerical resources were provided by the National Computational Infrastructure (NCI), under the National Computational Merit Allocation Scheme, which is supported by the Australian Government.
Publisher Copyright:
© 2019 by Gaetano M.D. Currao, Andrew J. Neely, Christopher M. Kennell, Sudhir L. Gai, and David R. Buttsworth.
PY - 2020
Y1 - 2020
N2 - This work presents an experimental and numerical study of hypersonic transitional shock-wave–boundary-layer interaction, wherein transition occurs between separation and reattachment in the detached shear layer. Experiments were conducted in a free-piston compression-heated Ludwieg tube that provided a Mach 5.8 flow at a freestream Reynolds number of 7 × 106 m−1. A shock generator deflected the flow by 10°, resulting in an oblique shock impinging on a flat plate. The shock triggered transition in the boundary layer and the formation of Görtler-like vortices downstream of reattachment. Heat flux and pressure distributions on the plate were measured globally using infrared thermography and pressure-sensitive paint. Oil film visualization was employed to evaluate the boundary-layer reattachment. Numerical results consist of Reynolds-averaged Navier–Stokes and fully laminar steady-state three-dimensional simulations. Shock-induced transition is considered to be the cause of the overshoot in peak pressure and peak heating of approximately 15%, in agreement with previous studies. Görtler instability, triggered by the concave nature of the bubble at separation, is identified as the main mechanism leading to boundary-layer transition, resulting in heat-flux variations of less than 30%. By comparing numerical results against thermographic values it is possible to delineate the extent of transition. Within this region, the disturbance amplification factor was estimated to be approximately between 6 and 10, in reasonable agreement with other relevant numerical and experimental data.
AB - This work presents an experimental and numerical study of hypersonic transitional shock-wave–boundary-layer interaction, wherein transition occurs between separation and reattachment in the detached shear layer. Experiments were conducted in a free-piston compression-heated Ludwieg tube that provided a Mach 5.8 flow at a freestream Reynolds number of 7 × 106 m−1. A shock generator deflected the flow by 10°, resulting in an oblique shock impinging on a flat plate. The shock triggered transition in the boundary layer and the formation of Görtler-like vortices downstream of reattachment. Heat flux and pressure distributions on the plate were measured globally using infrared thermography and pressure-sensitive paint. Oil film visualization was employed to evaluate the boundary-layer reattachment. Numerical results consist of Reynolds-averaged Navier–Stokes and fully laminar steady-state three-dimensional simulations. Shock-induced transition is considered to be the cause of the overshoot in peak pressure and peak heating of approximately 15%, in agreement with previous studies. Görtler instability, triggered by the concave nature of the bubble at separation, is identified as the main mechanism leading to boundary-layer transition, resulting in heat-flux variations of less than 30%. By comparing numerical results against thermographic values it is possible to delineate the extent of transition. Within this region, the disturbance amplification factor was estimated to be approximately between 6 and 10, in reasonable agreement with other relevant numerical and experimental data.
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U2 - 10.2514/1.J058718
DO - 10.2514/1.J058718
M3 - Article
AN - SCOPUS:85081173959
VL - 58
SP - 814
EP - 829
JO - AIAA Journal
JF - AIAA Journal
SN - 0001-1452
IS - 2
ER -