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

Frank Husmeier, Christian S J Mayer, Hermann F Fasel

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

7 Citations (Scopus)

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)
Title of host publication43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers
Pages9337-9349
Number of pages13
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

Fingerprint

Direct numerical simulation
Pressure gradient
Mach number
Boundary layers
Turbulence

ASJC Scopus subject areas

  • Engineering(all)

Cite this

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

Investigation of transition of supersonic boundary layers at mach 3 using DNS. / Husmeier, Frank; Mayer, Christian S J; Fasel, Hermann F.

43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers. 2005. p. 9337-9349.

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

Husmeier, F, Mayer, CSJ & Fasel, HF 2005, Investigation of transition of supersonic boundary layers at mach 3 using DNS. in 43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers. pp. 9337-9349, 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States, 1/10/05.
Husmeier F, Mayer CSJ, Fasel HF. Investigation of transition of supersonic boundary layers at mach 3 using DNS. In 43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers. 2005. p. 9337-9349
Husmeier, Frank ; Mayer, Christian S J ; Fasel, Hermann F. / Investigation of transition of supersonic boundary layers at mach 3 using DNS. 43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers. 2005. pp. 9337-9349
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