Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6

Jayahar Sivasubramanian, Hermann F Fasel

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

Abstract

Direct Numerical Simulations are performed to investigate the laminar-turbulent tran- sition in a boundary layer on a sharp cone at Mach 6. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. Towards this end, three breakdown mechanisms were considered, namely, the second-mode fundamental (K-type), subharmonic (N-/H-type) and oblique breakdown. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. Several small and medium scale simulations were carried out to explore the parameter space for fundamental and subharmonic resonance. These simulations indi- cated that for the chosen experimental conditions, the fundamental resonance was much stronger than subharmonic resonance. Subsequently a set of highly resolved fundamental and oblique breakdown simulations were performed. The nonlinear interactions observed during the breakdown process are discussed in great detail in this paper. A detailed de- scription of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer is also presented. These controlled transition simulations clearly demonstrate that both mechanisms, fundamental and oblique breakdown, may indeed be viable paths to complete breakdown to turbulence in hypersonic boundary layers at Mach 6.

Original languageEnglish (US)
Title of host publication51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
StatePublished - 2013
Event51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 - Grapevine, TX, United States
Duration: Jan 7 2013Jan 10 2013

Other

Other51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
CountryUnited States
CityGrapevine, TX
Period1/7/131/10/13

Fingerprint

Direct numerical simulation
Hypersonic boundary layers
direct numerical simulation
Mach number
Cones
boundary layers
cones
Boundary layers
boundary layer
breakdown
Turbulence
simulation
hypersonic boundary layer
Skin friction
Hypersonic aerodynamics
Flow structure
laminar-turbulent transition
turbulence
Heat transfer
flow structure

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Sivasubramanian, J., & Fasel, H. F. (2013). Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6. / Sivasubramanian, Jayahar; Fasel, Hermann F.

51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013.

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

Sivasubramanian, J & Fasel, HF 2013, Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6. in 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013, Grapevine, TX, United States, 1/7/13.
Sivasubramanian J, Fasel HF. Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013
Sivasubramanian, Jayahar ; Fasel, Hermann F. / Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6. 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013.
@inproceedings{bf442e4dc37742f082f8aa2ddeae41e7,
title = "Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6",
abstract = "Direct Numerical Simulations are performed to investigate the laminar-turbulent tran- sition in a boundary layer on a sharp cone at Mach 6. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. Towards this end, three breakdown mechanisms were considered, namely, the second-mode fundamental (K-type), subharmonic (N-/H-type) and oblique breakdown. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. Several small and medium scale simulations were carried out to explore the parameter space for fundamental and subharmonic resonance. These simulations indi- cated that for the chosen experimental conditions, the fundamental resonance was much stronger than subharmonic resonance. Subsequently a set of highly resolved fundamental and oblique breakdown simulations were performed. The nonlinear interactions observed during the breakdown process are discussed in great detail in this paper. A detailed de- scription of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer is also presented. These controlled transition simulations clearly demonstrate that both mechanisms, fundamental and oblique breakdown, may indeed be viable paths to complete breakdown to turbulence in hypersonic boundary layers at Mach 6.",
author = "Jayahar Sivasubramanian and Fasel, {Hermann F}",
year = "2013",
language = "English (US)",
isbn = "9781624101816",
booktitle = "51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013",

}

TY - GEN

T1 - Direct numerical simulation of controlled transition in a boundary layer on a sharp cone at Mach 6

AU - Sivasubramanian, Jayahar

AU - Fasel, Hermann F

PY - 2013

Y1 - 2013

N2 - Direct Numerical Simulations are performed to investigate the laminar-turbulent tran- sition in a boundary layer on a sharp cone at Mach 6. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. Towards this end, three breakdown mechanisms were considered, namely, the second-mode fundamental (K-type), subharmonic (N-/H-type) and oblique breakdown. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. Several small and medium scale simulations were carried out to explore the parameter space for fundamental and subharmonic resonance. These simulations indi- cated that for the chosen experimental conditions, the fundamental resonance was much stronger than subharmonic resonance. Subsequently a set of highly resolved fundamental and oblique breakdown simulations were performed. The nonlinear interactions observed during the breakdown process are discussed in great detail in this paper. A detailed de- scription of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer is also presented. These controlled transition simulations clearly demonstrate that both mechanisms, fundamental and oblique breakdown, may indeed be viable paths to complete breakdown to turbulence in hypersonic boundary layers at Mach 6.

AB - Direct Numerical Simulations are performed to investigate the laminar-turbulent tran- sition in a boundary layer on a sharp cone at Mach 6. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. Towards this end, three breakdown mechanisms were considered, namely, the second-mode fundamental (K-type), subharmonic (N-/H-type) and oblique breakdown. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. Several small and medium scale simulations were carried out to explore the parameter space for fundamental and subharmonic resonance. These simulations indi- cated that for the chosen experimental conditions, the fundamental resonance was much stronger than subharmonic resonance. Subsequently a set of highly resolved fundamental and oblique breakdown simulations were performed. The nonlinear interactions observed during the breakdown process are discussed in great detail in this paper. A detailed de- scription of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer is also presented. These controlled transition simulations clearly demonstrate that both mechanisms, fundamental and oblique breakdown, may indeed be viable paths to complete breakdown to turbulence in hypersonic boundary layers at Mach 6.

UR - http://www.scopus.com/inward/record.url?scp=84881421211&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84881421211&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84881421211

SN - 9781624101816

BT - 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

ER -