Experimental analysis of unsteady shock formation from interactions with turbulent features in a flat plate turbulent boundary layer
Final Report Abstract
The interaction between a turbulent boundary layer and a shock in a supersonic flow is studied using the particle image velocimetry (PIV) technique. Understanding the coupling mechanism between the boundary layer and the outer supersonic flow is fundamental in high-speed engineering applications. For example, the oscillations caused by the interaction can generate sufficient fatigue loading to lead to a catastrophic failure, such as structural damage in a supersonic vehicle. The experiments are conducted in a wind tunnel in which a flat plate is installed, and over which a turbulent boundary layer is formed. An oblique shock is generated outside the boundary layer and how the turbulent features within the boundary layer are modified as they interact with the impinging oblique shock is analysed. In particular, we focus on investigating the sources of flow oscillations that are orders of magnitude slower than the typical turbulent time scales, since the exact way in which these oscillations are generated is not well understood.
Publications
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Compressible flow regimes of a circular cylinder, Proc. 23rd Australas. Fluid Mech. Conf., 2022
M. Awasthi, S. McCreton, C. M. de Silva, R. Baidya, S. Scharnowski & C. J. Kähler
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Towards density measurements in a supersonic turbulent boundary layer, Proc. 20th Int. Symp. Laser Imaging Tech. Fluid Mech., 2022
R. Baidya, S. Scharnowski & C. J. Kähler
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Investigation of a near-field cylinder wake in the Mach number range 0.3 — 2 using highspeed PIV, Proc. 15th Int. Symp. Part. Image Velocimetry, 2023
R. Baidya, S. Scharnowski, M. Awasthi, C. M. de Silva & C. J. Kähler
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Investigation of a Near-Field Cylinder Wake in the Subsonic, Transonic, and Supersonic Regimes. AIAA Journal, 61(12), 5415-5428.
Baidya, Rio; Scharnowski, Sven; de Silva, Charitha M.; Awasthi, Manuj & Kähler, Christian J.
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Characterizing the transition between regular and Mach reflections induced by a shock wave–boundary layer interaction. Shock Waves, 35(2), 125-141.
Scharnowski, S.; Baidya, R. & Kähler, C. J.
