Investigation of transition of supersonic boundary layers at mach 3 using DNS

Frank Husmeier, Christian S.J. Mayer, Hermann F. Fasel

Research output: Contribution to conferencePaper

7 Scopus citations

Abstract

Several breakdown scenarios to turbulence of a supersonic flat-plate boundary layer with and without an adverse pressure gradient (APG) at Mach 3 are investigated using Direct Numerical Simulations (DNS). The effects of APG on an oblique breakdown and on "classical" fundamental and subharmonic breakdown mechanisms are studied. For the Mach number under investigation the boundary layer is most unstable with respect to a first mode three-dimensional wave according to Linear Stability Theory (LST). Therefore, "oblique" secondary instability mechanisms were investigated where both primary and secondary disturbance waves are three-dimensional. These breakdown mechanisms are scrutinized in order to gain insight with respect to their relevance for practical applications.

Original languageEnglish (US)
Pages9337-9349
Number of pages13
StatePublished - Dec 1 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

ASJC Scopus subject areas

  • Engineering(all)

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    Husmeier, F., Mayer, C. S. J., & Fasel, H. F. (2005). Investigation of transition of supersonic boundary layers at mach 3 using DNS. 9337-9349. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.