Numerical investigation of laminar-turbulent transition for a flared cone at Mach 6

Jayahar Sivasubramanian, Hermann F Fasel

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

3 Citations (Scopus)

Abstract

Spatial Direct Numerical Simulations (DNS) were performed to investigate Laminar– turbulent transition for a flared cone at Mach 6. The flow parameters used in the simulations closely match the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. The objective of the present research is to make a contribution towards understanding of the nonlinear stages of transition in hypersonic boundary layers on a flared cone. In particular, towards understanding the effect of the adverse pressure gradient on the nonlinear stages of transition. To this end, the role of second–mode fundamental (K-type) and oblique breakdown is investigated using controlled transition simulations. For fundamental resonance, the parameter space was first explored by performing several low-resolution simulations in order to identify the cases that result in the strongest nonlinear interactions. Subsequently, a set of highly resolved fundamental and oblique breakdown simulations have been performed and the results are presented in this paper. Both second–mode fundamental and oblique breakdown lead to strong nonlinear interactions and were thus found to be viable candidates of nonlinear mechanisms that can lead to a fully turbulent boundary layer. The nonlinear interactions observed during these breakdown processes are discussed in detail. A detailed description of the flow structures that arise due to these nonlinear interactions is provided and the development of the skin friction and heat transfer during the breakdown is presented.

Original languageEnglish (US)
Title of host publication54th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103933
StatePublished - 2016
Event54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States
Duration: Jan 4 2016Jan 8 2016

Other

Other54th AIAA Aerospace Sciences Meeting, 2016
CountryUnited States
CitySan Diego
Period1/4/161/8/16

Fingerprint

Mach number
Cones
Hypersonic boundary layers
Skin friction
Hypersonic aerodynamics
Direct numerical simulation
Flow structure
Pressure gradient
Boundary layers
Heat transfer
Experiments

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Sivasubramanian, J., & Fasel, H. F. (2016). Numerical investigation of laminar-turbulent transition for a flared cone at Mach 6. In 54th AIAA Aerospace Sciences Meeting American Institute of Aeronautics and Astronautics Inc, AIAA.

Numerical investigation of laminar-turbulent transition for a flared cone at Mach 6. / Sivasubramanian, Jayahar; Fasel, Hermann F.

54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016.

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

Sivasubramanian, J & Fasel, HF 2016, Numerical investigation of laminar-turbulent transition for a flared cone at Mach 6. in 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 54th AIAA Aerospace Sciences Meeting, 2016, San Diego, United States, 1/4/16.
Sivasubramanian J, Fasel HF. Numerical investigation of laminar-turbulent transition for a flared cone at Mach 6. In 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA. 2016
Sivasubramanian, Jayahar ; Fasel, Hermann F. / Numerical investigation of laminar-turbulent transition for a flared cone at Mach 6. 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016.
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