Numerical investigation of laminar-turbulent transition in a cone boundary layer at Mach 6

Jayahar Sivasubramanian, Hermann F Fasel

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

6 Citations (Scopus)

Abstract

Laminar-Turbulent transition in a hypersonic cone boundary layer is investigated using Direct Numerical Simulations (DNS). The flow parameters used in the simulations are based on the experimental conditions of the Boeing/AFOSR Mach 6 quiet-flow Ludwieg Tube at Purdue University. The main objective of the present research is to determine which nonlinear mechanisms may be dominant in a broad band "natural" disturbance environment and then to perform controlled transition simulations of these mechanisms. Towards this end, a "natural" transition scenario was modeled and investigated by generating wave packet disturbances. These wave packet simulations provided strong evidence for a possible presence of fundamental and subharmonic resonance mechanisms in the nonlinear transition regime. However, the fundamental resonance was much stronger than the subharmonic resonance. To gain more insight into the nonlinear development we performed controlled transition simulations of these mechanisms. We found that the strength of fundamental resonance is strongly influenced by the wave angle of the secondary oblique wave pair. For a conical geometry this issue is even more complicated than for a flat-plate as the wave angle of a disturbance wave changes in the downstream direction. Therefore, first we carried out a parameter study to find the most strongly resonating oblique wave pair. Then a set of highly resolved controlled fundamental (K-type) breakdown simulations was performed using the most strongly resonating oblique wave pair as secondary waves. These simulations demonstrated that fundamental breakdown may indeed be a viable path to complete breakdown to turbulence in hypersonic cone boundary layers.

Original languageEnglish (US)
Title of host publication41st AIAA Fluid Dynamics Conference and Exhibit
StatePublished - 2011
Event41st AIAA Fluid Dynamics Conference and Exhibit 2011 - Honolulu, HI, United States
Duration: Jun 27 2011Jun 30 2011

Other

Other41st AIAA Fluid Dynamics Conference and Exhibit 2011
CountryUnited States
CityHonolulu, HI
Period6/27/116/30/11

Fingerprint

Mach number
Cones
Boundary layers
Wave packets
Hypersonic aerodynamics
Direct numerical simulation
Pipe flow
Turbulence
Geometry

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Mechanical Engineering

Cite this

Sivasubramanian, J., & Fasel, H. F. (2011). Numerical investigation of laminar-turbulent transition in a cone boundary layer at Mach 6. In 41st AIAA Fluid Dynamics Conference and Exhibit

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

41st AIAA Fluid Dynamics Conference and Exhibit. 2011.

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

Sivasubramanian, J & Fasel, HF 2011, Numerical investigation of laminar-turbulent transition in a cone boundary layer at Mach 6. in 41st AIAA Fluid Dynamics Conference and Exhibit. 41st AIAA Fluid Dynamics Conference and Exhibit 2011, Honolulu, HI, United States, 6/27/11.
Sivasubramanian J, Fasel HF. Numerical investigation of laminar-turbulent transition in a cone boundary layer at Mach 6. In 41st AIAA Fluid Dynamics Conference and Exhibit. 2011
Sivasubramanian, Jayahar ; Fasel, Hermann F. / Numerical investigation of laminar-turbulent transition in a cone boundary layer at Mach 6. 41st AIAA Fluid Dynamics Conference and Exhibit. 2011.
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