New experimental data of STBLI at DNS/LES accessible reynolds numbers

Patrick Bookey, Christopher Wyckham, Alexander Smits, M. Pino Martin

Research output: Contribution to conferencePaperpeer-review

91 Scopus citations


An experimental investigation was conducted to study four shock/turbulent boundary layer interactions. In Mach 2.9 flow, a 24° compression corner and a 12° reflected shock interaction were studied at Reθ = 2400. In a Mach 8 flow, an 8° compression corner and a 10° sharp fin were studied at Reθ = 3500. These low Reynolds number flows were chosen to coincide with DNS accessible Reynolds numbers in order to make direct comparisons. Measurements included mean flow surveys, surface pressure distributions, surface flow visualizations and Filtered Rayleigh Scattering (FRS). FRS was used to make two-dimensional images of the flow in the streamwise direction giving a qualitative picture of the nature of the interaction. Statistical data of the boundary layer characteristics was also obtained from the FRS images. The results show the incoming boundary layer at both Mach numbers to be fully turbulent. The interactions in Mach 2.9 flow produced large areas of separation. The compression ramp in the Mach 8 flow was found to remain attached throughout the interaction, while the 10° sharp fin produced a large three-dimensional separated region. The preliminary results indicate good agreement between experiment and DNS computations.

Original languageEnglish (US)
Number of pages18
StatePublished - 2005
Event43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 10 2005Jan 13 2005


Other43rd AIAA Aerospace Sciences Meeting and Exhibit
Country/TerritoryUnited States
CityReno, NV

All Science Journal Classification (ASJC) codes

  • General Engineering


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