Laminar/Transitional Fin-Induced Shock Boundary Layer Interactions on a Hollow Cylinder at Mach 5

Abstract

Fin-induced Shock Boundary Layer Interactions (SBLIs) are investigated on a hollow cylinder at Mach 5 across a range of Reynolds numbers $1.27\times 10^6 < {Re}_{ x_{f}} < 4.90\times 10^6$. Unsteady pressure measurements demonstrate that the incoming boundary layer contains transitional features for all cases. Infrared thermography (IRT) is used to measure surface heat transfer characterizing the global structure of the SBLI. IRT results show transitional behavior within SBLI, with a downstream shift in separation location and the development of secondary separation for the highest Reynolds number case (${Re}_{x_{f}} = 4.90\times 10^6$). An elevated region of surface heat transfer is observed near reattachment for all cases but is segmented at low Reynolds numbers. RMS pressure levels and spectra within the SBLI increase with an increase in Reynolds number. The highest Reynolds number case (${Re}_{x_{f}} = 4.90\times 10^6$) demonstrates low frequency unsteadiness near reattachment and significantly greater unsteadiness throughout the SBLI.