Analysis of shockwave/turbulent boundary layer interaction using DNS and experimental data

M. Wu, P. Bookey, M. P. Martin, A. J. Smits

Research output: Contribution to conferencePaper

5 Scopus citations

Abstract

Shockwave/turbulent boundary layer interactions are studied by comparing direct numerical simulation and experimental data. Two canonical configurations, a 24-degree compression ramp and shock impinging a wall with reflection, are studied. The Mach number for the incoming boundary layer is 2.9. Re θ in the numerical simulation is 2400. Two experimental data sets are used, namely those of Bookey et al1 at the same flow conditions as the DNS and those of Selig3 at Reg of about 70,000. Mean velocity profiles, wall pressure distribution, mass flux turbulence intensity, 2D density correlation and locations of the flow separation and reattachment are compared. In addition, an analysis of the turbulence structure characteristics for the DNS data is given.

Original languageEnglish (US)
Pages1629-1648
Number of pages20
DOIs
StatePublished - 2005
Event43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 10 2005Jan 13 2005

Other

Other43rd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/10/051/13/05

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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    Wu, M., Bookey, P., Martin, M. P., & Smits, A. J. (2005). Analysis of shockwave/turbulent boundary layer interaction using DNS and experimental data. 1629-1648. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States. https://doi.org/10.2514/6.2005-310