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

• Published in: AIAA journal 2017-09, Vol.55 (9), p.2919-2928
• Main Authors: Pizzella, Miranda, Warning, Sally, Jennerjohn, Mary, McQuilling, Mark, Purkey, Ashley, Scharnhorst, Richard, Mani, Mori
• Format: Article
• Language: English
• Subjects: Aspect ratio; Boundary layer interaction; Compression waves; Computational fluid dynamics; Corner flow; Inlets; Longitudinal waves; Normal shock waves; Separation; Shock wave interaction; Spalart-Allmaras turbulence model; Stokes flow; Supersonic wind tunnels; Three dimensional flow; Turbulence models; Uniform flow; Wind tunnel testing
• ISSN: 0001-1452; 1533-385X
• DOI: 10.2514/1.J055592

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 show the corner separation generates compression waves and reflected shocks, which disrupt spanwise uniformity. The geometric aspect ratio contributes to the placement and structure of the corner flow phenomena, which affects the intended shock structure across the centerline. A three-dimensional representation of the flowfield is produced, providing a cause-and-effect analysis of the three-dimensionality of the flow, which gives new, physical understanding of the shock and separation behavior in a large-aspect-ratio test section.