Experimental Characterization of Supersonic Flow over a Wall-Mounted Hemisphere

What is it about?

The shockwave boundary-layer interactions associated with the flow over aircraft protrusions is of significant interest to the aerospace community. The unsteadiness in the flow field over such aircraft protrusions might not only compromise their structural integrity by inducing structural vibrations and fatigue but can also lead to degraded performance of the instrumentation they house. The protrusions are generally modeled as wall-mounted bluff bodies of simple geometry such as a cylinder, hemisphere, or hemisphere-cylinder. In the present study, supersonic flow over a wall-mounted hemisphere is experimentally investigated to understand the shock wave boundary layer interactions, flow separation, and other complex flow features associated with it.

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