Shock-Wave/Boundary-Layer Interaction in a Large-Aspect-Ratio Test Section

Shock-wave/boundary-layer interactions occurring in the inlets cause degradation of inlet efficiency. To better control these interactions and improve inlet performance, shock-wave/boundary-layer interactions need to be tested in supersonic wind tunnels in a region of clean, uniform flow. Wind tunnels used to study shock-wave/boundary-layer interactions generally have small rectangular test sections containing corner flow that affect the shock-wave/boundary-layer interactions. It is hypothesized that extending the width of the test section to increase the aspect ratio (test section inlet width W to height H) may deter corner flow from influencing the centerline flow. This study uses a Reynolds-averaged Navier–Stokes flow solver (Wind-US 3.0) with the Spalart–Allmaras turbulence model to investigate a normal shock-wave/boundary-layer interaction at Mach 1.6 in a 4.3-aspect-ratio test section. The analysis is focused on the spanwise composition of the shock-wave/boundary-layer interaction, where results sho...