Wall-pressure measurements in a mach 3 shock-wave turbulent boundary layer interaction at a DNS-accessible reynolds number

Matthew J. Ringuette, Alexander J. Smits

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

3 Scopus citations

Abstract

Experiments are performed to investigate the fluctuating wall pressure in a Mach 2.9 shock-wave turbulent boundary layer interaction with a low Reynolds number based on momentum thickness of 2400. This Reynolds number is accessible to present direct numerical simulations (DNS), so that the data can be used for DNS validation. The configuration studied is a nominally two-dimensional 24° compression corner. Compared to data at higher Reynolds numbers (of order 104-105), the results show a smaller peak in the RMS of the pressure fluctuations. The wall-pressure signal does not exhibit the large degree of intermittency found in the shock-foot region at higher Reynolds numbers. Spectra show that the signal energy is more distributed over the range of shock oscillation frequencies, resulting in a smaller peak energy as compared to data at high Reynolds numbers. The shock motion has a broadband frequency distribution with a peak slightly below 1 kHz, similar to that seen in higher Reynolds number flows. The mean-wall pressure distribution, RMS pressure fluctuation profile, wall-pressure signal, and shock-motion frequency agree well with a DNS performed at matching conditions.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - 37th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
Pages944-957
Number of pages14
ISBN (Print)1563478978, 9781563478970
DOIs
StatePublished - Jan 1 2007
Event37th AIAA Fluid Dynamics Conference - Miami, FL, United States
Duration: Jun 25 2007Jun 28 2007

Publication series

NameCollection of Technical Papers - 37th AIAA Fluid Dynamics Conference
Volume2

Other

Other37th AIAA Fluid Dynamics Conference
CountryUnited States
CityMiami, FL
Period6/25/076/28/07

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Engineering (miscellaneous)

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    Ringuette, M. J., & Smits, A. J. (2007). Wall-pressure measurements in a mach 3 shock-wave turbulent boundary layer interaction at a DNS-accessible reynolds number. In Collection of Technical Papers - 37th AIAA Fluid Dynamics Conference (pp. 944-957). (Collection of Technical Papers - 37th AIAA Fluid Dynamics Conference; Vol. 2). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2007-4113