Experimental Investigation of Embedded Shear Layer in Smooth-body Separated Flow over Boeing Bump

This study is focused on the experimental characterization of smoothbody flow separation over the Boeing Bump for an incompressible turbulent boundary layer with Re = 5.0×103, corresponding to a freestream Mach number of M∞ = 0.2. The mean separation bubble was documented to decrease in wall normal and streamwise extent with spanwise distance from the tunnel centerline. The turbulent shear stress was documented to be maximal at the outer inflection point of the centerline mean velocity profile within the separation bubble region. Embedded shear layer scaling on the mean velocity and turbulence intensities exhibit similarity over a large wall-normal extent, with the only deviation occurring in the near-wall region. Herein, we partition an embedded shear layer scaling into two regions, with new scaling near the wall, which allows further similarity of the turbulence intensity profiles towards the wall surface.