Hypersonic Boundary Layer with Streamline Curvature-Driven Adverse Pressure Gradient
2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The effects of a streamline curvature-induced adverse pressure gradient on a Mach 4.9 turbulent boundary layer were investigated using particle image velocimetry. The current geometry has impulse parameters of Ip = 0.47 and I = 0.13. The effect of the pressure gradient on the mean velocity and Reynolds stress fields is characterized and the extent of this destabilization is compared with previous studies. High resolution planar vector fields have been acquired for both a baseline zero pressure gradient model, as well as an adverse pressure gradient model. As expected the peak Reynolds shear stress amplification was 160%. Quadrant decomposition of the data also showed a shift in organization to Quadrant 4 indicating a strengthening of the sweep events.