Influence of Perturbations on 3-D Hypersonic Shock Laminar Boundary Interactions
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2017 by Leidy, Neel, Bowersox, Schmisseur. An experimental campaign focused on probing the response of laminar and disturbed hypersonic boundary layers to a shock wave is underway. The set of experiments presented in this paper were conducted at Mach 6 and 7 in the Adjustable Contour Expansion Tunnel, where the freestream turbulence levels range from 0.1% to 1.5% at the tested conditions. The test-bed for the study was a slightly blunted, 1.3-degree half-angle, wedge that incorporates NASA pizza box trips to create disturbances. A cylinder was mounted at different streamwise locations to induce shock interactions on the boundary layer. This paper presents surface oil flow images, which initially indicated the necessity to revamp, and later fine-tune, the model design and now reveal some key features of the shock wave/boundary layer interaction. Infrared thermography allows for the surface heat flux which provides data outside and within the separated region. Surface mounted PCB and Kulite pressure sensors map out the state of the incoming boundary layer, the influence of the trip perturbations, and the extent of the interaction.
