Experimental and Computational Evaluation of Smooth-Body Separated Flow over Boeing Bump

The current progress on the smooth-body separation experiment being conducted on the Boeing bump model at the University of Notre Dame is reported on. Hot-wire anemometry was used to obtain boundary layer velocity profiles upstream of the bump, pressure ports were used to measure the static pressure field over the bump, and stereoscopic particle image velocimetry was used to measure three-component velocity and turbulence fields in the separated flow region. Experimental and simulation data were reported for a Reynolds number of Re_L = 4.0 × 10⁶, based on inlet freestream and test section width L. Two streamwise bump configurations were studied - with the bump apex located L and 2L downstream from the boundary layer development plate leading edge. Reynolds-averaged Navier-Stokes and delayed detached eddy simulations were run blindly for several grid cases and compared to the selected test data. This work is a sample of the validation data, which are archived on the NASA Turbulence Modeling Resource website.