On the Effect of Test Section Aspect Ratio for Shock Wave - Boundary Layer Interactions

© 2017 by the American Institute of Aeronautics and Astronautics, Inc. Many test sections used to study shock wave boundary layer interaction (SBLI) phenomena employ rectangular geometries which exhibit various levels of three-dimensionality in the generated shock structure. Previous studies have suggested the three-dimensional nature to be heavily influenced by the compression fans generated by the corner separation. It is hypothesized test section geometry has a large influence on the flowfield due to the role it plays on how the compression fans will affect the SBLI. This study uses a Reynolds-averaged Navier-Stokes flow solver to investigate the effect of test section aspect ratio (width/height) for a normal SBLI at Mach 1.6. Geometries include an aspect ratio of 4.3 (10.635” x 2.462”), and two 2 aspect ratios (4.924” x 2.462” and 10.635” x 5.3175”). Analysis is focused on how the test section height influences the compression fans generated by corner flow blockage. Two flow states governed by a viscous height ratio (δ* /H) are used to describe the corner shock system. Additionally, a Buckingham Pi analysis was performed using simulation data of oblique SBLIs to determine physics-based functional relationships relating geometric and fluid dynamic parameters important to SBLIs. This paper provides insight on geometric influences on SBLIs and serves as a reference for SBLI test designs.