TY - GEN
T1 - Numerical Investigation of Boundary-Layer Transition initiated by Random Disturbances for 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 (University of Arizona) for his support with the LST analysis.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - Direct Numerical Simulations (DNS) were carried out in order to investigate the laminarturbulent 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. Previous results from three-dimensional nonlinear wave packet simulations indicated that all the "classical" nonlinear mechanisms (fundamental resonance, oblique breakdown, subharmonic resonance) may be relevant for a hypersonic boundary-layer transition on a flat plate. For the present laminar-turbulent transition investigation, a random forcing approach is employed, which has been previously used as a model for "natural" transition without any bias towards a particular nonlinear mechanism.
AB - Direct Numerical Simulations (DNS) were carried out in order to investigate the laminarturbulent 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. Previous results from three-dimensional nonlinear wave packet simulations indicated that all the "classical" nonlinear mechanisms (fundamental resonance, oblique breakdown, subharmonic resonance) may be relevant for a hypersonic boundary-layer transition on a flat plate. For the present laminar-turbulent transition investigation, a random forcing approach is employed, which has been previously used as a model for "natural" transition without any bias towards a particular nonlinear mechanism.
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U2 - 10.2514/6.2022-1580
DO - 10.2514/6.2022-1580
M3 - Conference contribution
AN - SCOPUS:85123629679
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -