Flow Characterization over a Modified Boeing Bump

This experimental study characterized the flow over a modified Boeing bump at Reynolds numbers based on bump height (Re_ℎ) ranging from 1.3 × 10^4 to 8.8 × 10^4. Removable inserts are included to make the facility adaptable for future flow control approaches. For now, the inserts are employed to incorporate different sensor arrays. High-frequency pressure and wall shear stress measurements are conducted on the upstream and downstream sides of the bump, while oil flow visualization is performed on the downstream side to capture the three-dimensional surface flow topology and identify flow features. Pressure measurements show lower mean values downstream of the bump than the upstream side indicating flow separation. Skin friction measurements supported the pressure results, showing larger values of wall shear stress in the upstream region. Additionally, the skin friction coefficient (��_�� ) decreases with increasing ����_ℎ accordingly to literature data with larger uncertainty at lower freestream conditions. Oil flow visualization captures flow separation on the bump. Spectral analysis of pressure data in the downstream region shows periodic motions in the separated flow. Correlation between the different measurements techniques and surface flow visualization were observed. They will serve for informing future experiments that will focus on integrating metamaterial for mitigation of flow separation.