Volumetric study of a turbulent boundary layer and swept impinging oblique SBLI at mach 2.3

James A.S. Threadgill, Jesse C Little

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Scopus citations

Abstract

A swept impinging oblique Shock Boundary Layer Interaction (SBLI) is investigated in Mach 2.3 flow induced by a shock generator with sweep ψ = 30.0° and x-y plane deflection of θ = 12.5°. The incoming flow is a naturally turbulent boundary layer developing over the flat wind tunnel wall with Reθ = 5.5 × 103. A combination of Stereo PIV and Tomographic PIV is used to characterize both the undisturbed incoming boundary layer and the resultant complex geometries of the swept SBLI. Linear Stochastic Estimation is used to identify statistically significant boundary layer vortical structures and document changes to their topology at various heights in the boundary layer. Three-dimensional velocity snapshots throughout the swept SBLI show both large-scale growth/collapse of the interaction and prominent streamwise streaks with a notable spanwise periodicity. Finally the mean structure for this configuration is documented for the first time. This is an initial summary of a large PIV data set (over 3 TB) that already provides a valuable contribution to the understanding of this complex flow.

Original languageEnglish (US)
Title of host publication2018 Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105531
DOIs
StatePublished - Jan 1 2018
Event48th AIAA Fluid Dynamics Conference, 2018 - Atlanta, United States
Duration: Jun 25 2018Jun 29 2018

Other

Other48th AIAA Fluid Dynamics Conference, 2018
CountryUnited States
CityAtlanta
Period6/25/186/29/18

ASJC Scopus subject areas

  • Aerospace Engineering
  • Engineering (miscellaneous)

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  • Cite this

    Threadgill, J. A. S., & Little, J. C. (2018). Volumetric study of a turbulent boundary layer and swept impinging oblique SBLI at mach 2.3. In 2018 Fluid Dynamics Conference [AIAA 2018-3707] American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-3707