TY - GEN
T1 - Direct numerical simulations of the nonlinear boundary layer transition regime on a flat plate at mach 6
AU - Leinemann, Madlen
AU - Hader, Christoph
AU - Fasel, Hermann F.
N1 - Funding Information:
This work was supported by AFOSR Grant FA9550-19-1-0208, with Dr. Sarah Popkin serving as the program manager. Computer time was provided by the US Army Engineering Research and Development Center (ERDC) under the Department of Defense (DOD) High Performance Computing Modernization Program (HPCMP). The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the Air Force Office of Scientific Research or the U. S. Government. The authors would like to thank Anthony Haas for providing the LST code.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Direct Numerical Simulations (DNS) were carried out in order to investigate the laminar-turbulent transition process of a hypersonic boundary-layer on a flat plate. The conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University were used for the simulations. Results from a three-dimensional nonlinear wave packet simulation indicated that all of the “classical” nonlinear mechanisms (fundamental resonance, subharmonic resonance, oblique breakdown) are possible breakdown scenarios for a hypersonic boundary-layer on a flat plate. A detailed investigation of the secondary instability regime showed that the fundamental resonance was much stronger than the subharmonic resonance. High-fidelity “controlled” breakdown simulations for first mode oblique and second mode fundamental, exhibited the development of “hot” streak patterns on the surface of the flat plate. Streamwise “hot” streaks were also observed in the flared cone experiments at the BAM6QT facility and in DNS of high-speed transition for straight and flared cones. For the flat plate the fundamental resonance and the oblique breakdown mechanisms lead to a breakdown to turbulence. The transition region of the second mode fundamental breakdown is longer than for the first mode oblique breakdown.
AB - Direct Numerical Simulations (DNS) were carried out in order to investigate the laminar-turbulent transition process of a hypersonic boundary-layer on a flat plate. The conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University were used for the simulations. Results from a three-dimensional nonlinear wave packet simulation indicated that all of the “classical” nonlinear mechanisms (fundamental resonance, subharmonic resonance, oblique breakdown) are possible breakdown scenarios for a hypersonic boundary-layer on a flat plate. A detailed investigation of the secondary instability regime showed that the fundamental resonance was much stronger than the subharmonic resonance. High-fidelity “controlled” breakdown simulations for first mode oblique and second mode fundamental, exhibited the development of “hot” streak patterns on the surface of the flat plate. Streamwise “hot” streaks were also observed in the flared cone experiments at the BAM6QT facility and in DNS of high-speed transition for straight and flared cones. For the flat plate the fundamental resonance and the oblique breakdown mechanisms lead to a breakdown to turbulence. The transition region of the second mode fundamental breakdown is longer than for the first mode oblique breakdown.
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M3 - Conference contribution
AN - SCOPUS:85100081980
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 20
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -