Investigation of Oblique Breakdown in a Supersonic Boundary Layer at Mach 2 Using DNS

Mayer, Christian S. J.; Wernz, Stefan; Fasel, Hermann F.

doi:10.2514/6.2007-949

Cited by 25 publications

(34 citation statements)

References 7 publications

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“…For example, Thumm (1991) and Fasel et al (1993) found the so-called "oblique breakdown" for a boundary layer at Mach 1.6. This breakdown mechanism is initiated by the nonlinear interaction of two oblique instability waves with equal but opposite wave angles (see, e.g., Adams & Kleiser, 1993;Sandham et al, 1995;Eissler & Bestek, 1996;Fezer & Kloker, 1999;Husmeier et al, 2005;Mayer et al, 2007Mayer et al, , 2008Mayer et al, , 2009). Kosinov and co-workers (Kosinov et al, 1994b,a;Ermolaev et al, 1996;Kosinov et al, 1997) investigated the nonlinear transition regime of a supersonic boundary layer and reported a different breakdown mechanism, which they called "asymmetric subharmonic resonance."…”

Section: Scope Of Present Researchmentioning

confidence: 99%

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Sivasubramanian

2011

41st AIAA Fluid Dynamics Conference and Exhibit

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Section: Scope Of Present Researchmentioning

confidence: 99%

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Sivasubramanian

2011

41st AIAA Fluid Dynamics Conference and Exhibit

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“…These results are concerned to the smooth surface of the flat plate. According to the calculations [22], one of the competing transition mechanisms of two-dimensional supersonic boundary layer is the so-called oblique breakdown. Earlier it was experimentally revealed that subharmonic resonance is playing a leading role in the process of transition in supersonic boundary layer, and the mechanism of oblique breakdown significantly behind in competition with subharmonic type of transition.…”

Section: Introductionmentioning

confidence: 99%

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

Panina

Kosinov

Семёнов

et al. 2017

AIP Conference Proceedings

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Abstract.The results of an experimental study of the controlled pulsations development in the spanwise modulated boundary layer of a swept wing are presented in the paper. The experiments were conducted at Mach 2 and unit Reynolds number Re1 = 6×10 6 m -1 . The square stickers were applied to induce the spanwise modulation of mean flow in the boundary layer. It was obtained, that the presence of roughness leads to a decrease of the disturbance source efficiency at the subharmonic and fundamental frequency, and the oblique breakdown mechanism begins to appear at smaller values of the longitudinal coordinate x as compared with the case of a smooth wing.

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“…Although in CASE 4, an additional two-dimensional mode ( [1,0]) with the fundamental frequency is forced in order to broaden the disturbance spectrum, final breakdown to turbulence is not enhanced when compared to CASE 3. For CASE 4, the skin-friction coefficient in figure 5.23b…”

Section: Final Breakdown To Turbulencementioning

confidence: 99%

Numerical Simulation of Transition in Hypersonic Boundary Layers

Fasel¹,

Groß²,

Koevary³

et al. 2011

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The public reportmg burd en for th1s collection of mform ation is estimated to average 1 hour per response. includmg the tim e for rev>ewing instruct>ons. searclhing exi sting data so urces. gathering and mmnta1mng the data needed . and co mpleting and rev1ew 1 ng the collection of 1nforma t1 on. Send co mments regarding th1s burden est1m ate or any other aspect o fth1s collection of mformat1on . 1nclud1 ng suggesti ons for reduc1 ng the burden. to the Department of De fense. ExecutiV e Serv1ce D>rectorate (0704 -0 188) Respo ndents should be aware that notwithstanding any other prov1 s1 on of law. no person shall be sub;ect to any penalty for falling to comply w1th a collect> on of 1 nform at1on if 1 t does not display a currently v alid OMB co ntrol number PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ORGANIZATION. 1. REPORT DATE (DD-MM-YYYY)12. REPORT TYPE 3. DATES COVERED (From-To) SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Office of Scientific Research, AFOSR/RSA 4015 Wilson Blvd., Room 713, Arlington, VA 22203 SPONSOR/MONITOR'S REPORT NUMBER(S)AFRL-OSR-VA-TR-2012-0255 DISTRIBUTION/AVAILABILITY STATEMENTA -Approved For Public Release; Distribution is Unlimited. SUPPLEMENTARY NOTES ABSTRACTThe laminar-turbulent transition process in supersonic and hypersonic boillldary layers was investigated using spatial and temporal Direct Numerical Simulations (DNS). Our previous research indicated that oblique breakdown might be a highly relevant nonlinear mechanism for supersonic boillldary layers. However, a nonlinear mechanism would only be relevant for the transition process if this mechanism can lead to fully developed turbulence. Hence, to address this question, the late nonlinear transition regime of a supersonic flat-plate boillldary layer at Mach 3 was studied using spatial DNS. These simulations demonstrated that a fully turbulent flow can develop via oblique breakdown. We also investigated the nonlinear disturbance development in a hypersonic bolUldary layer on a sharp circular cone at Mach 8 using spatial and temporal DNS. It was confirmed in these simulations that fimdamental resonance and oblique breakdown are the viable paths to transition in hypersonic boillldary layers. 1S. SUBJECT TERMS

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Investigation of Oblique Breakdown in a Supersonic Boundary Layer at Mach 2 Using DNS

Cited by 25 publications

References 7 publications

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

Numerical Simulation of Transition in Hypersonic Boundary Layers

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