Supersonic flow over a wall-mounted hemisphere was experimentally investigated to understand the shock-wave/boundary-layer interactions, flow separation, and other complex flow features associated with it. The experiments were carried out on a hemisphere mounted on the wind-tunnel floor at Mach 2 and a Reynolds number of 3.6 million. Measurements include oil flow visualizations, shadowgraph visualizations, and steady and unsteady pressure distributions on the floor and the hemisphere. Although the supersonic flow around the hemisphere and the shock/boundary-layer interactions associated with it share some similarities with well-documented supersonic flows over wall-mounted blunt bodies like cylinders and blunt fins, some marked differences unique to the hemisphere were noticeable in the present study. The triple point of the -shock structure formed ahead of the hemisphere due to the interaction between the separation shock and the bow shock made a significant excursion over the hemisphere. The excursion of the triple point over the hemisphere closely correlated with the movement of the separation shock rather than the bow shock. Strong vortex structures seemed to form at the foot of the reattachment bow shock repetitively and convect over the hemisphere. Unsteady pressure measurement results provided useful insights on the distribution of flow unsteadiness over the hemisphere.
Experimental Characterization of Supersonic Flow over a Wall-Mounted Hemisphere
AIAA Journal ; 59 , 11 ; 4486-4500
2021-07-19
15 pages
Article (Journal)
Electronic Resource
English
Parametric Study of Supersonic Flow Over a Wall-Mounted Hemisphere (AIAA 2018-1786)
British Library Conference Proceedings | 2018
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