Numerical study of a shock-wave boundary-layer interaction: compression ramp flow-fields

Shock-wave boundary-layer interaction (SBLI) causes a serious aerodynamic and structural problems, therefore understanding its complex flow phenomenon is essential. Flow properties at the interaction region were numerically predicted via solving steady, compressible, 2D Navier-Stokes Equations with Roe-FDS flux type and a second order upwind flow discretization. Two compression ramps with 12° and 24° angles were investigated. The flow over a 12° ramp were fully attached with a λ-shock type and a limited upstream influence. Wall temperature increases to 2.55 times the edge temperature value and affected region increases with the downstream distance. The pressure field for the 24° ramp case reveals a substantial increase in the upstream influence due to the strong shock. A larger shock-leg at the wall provoke a significant flow separation and the wall temperature increases to 2 times the edge temperature value. Separation bubble is generated at the corner, with a separation length of 3.25 times the boundary layer thickness. This leads to a noticeable increase in the total pressure drag. Simulated results were fairly agreeing with the experimental result at the separation region. (paper)