Experiments have been conducted in a supersonic rectangular duct (Mach 1.4), with a normal shock wave/boundary layer interaction. The duct is designed in a modular fashion so that its aspect ratio can be varied without a change in the flow geometry. The shock location, duct height, and Mach number are kept constant, while varying the aspect ratio. Conventional and inclined schlieren techniques have been used to visualize the normal shock. The height and width of the “normal part” of the normal shock have been measured. A parameter termed area fraction of the normal shock is used to quantify the extent of shock bifurcation, and the effect of the duct aspect ratio on this parameter is studied. It has been found that a nearly square duct is the preferred geometry for maximizing the area fraction of the normal shock.
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Communicated by S. O'Byrne and A. Higgins.
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Vaisakh, S., Namratha, P.R. & Muruganandam, T.M. Effect of duct aspect ratio on normal shock wave/boundary layer interaction. Shock Waves 30, 215–219 (2020). https://doi.org/10.1007/s00193-019-00929-9
- Supersonic flow
- Shock wave/boundary layer interaction
- Duct flow
- Duct aspect ratio
- Boundary layer separation