Spatial Evolution of Mean Flow Properties in Supersonic Boundary Layers of Adiabatic and Isothermal Curved Surfaces Including Shock Interactions

This study investigates supersonic boundary layers over a turbine cascade under the coupled influence of surface curvature, streamwise pressure gradients, and shock-boundary layer interactions (SBLIs), for both adiabatic and isothermal (cooled, $T_w/T_{\infty}=0.75$) wall conditions. Wall-resolved large eddy simulations are performed at an inlet Mach number $M_\infty = 2.0$ and Reynolds number $Re_\infty = 200\,000$. Results show that wall cooling increases near-wall density, reduces temperature and viscosity, and yields fuller streamwise momentum profiles, making the boundary layer more resistant to separation and reducing the scale of the suction-side SBLI. The curvature-induced pressure gradients, favorable on the suction side and adverse on the pressure side, govern the thermodynamic response, causing flow expansion and compression, respectively. A balance analysis reveals that compressibility effects dominate the streamwise evolution of momentum upstream of the SBLIs, while downstream recovery is primarily driven by turbulent transport and mean advection rather than the local pressure gradient.