TY - GEN
T1 - Direct numerical simulations of the nonlinear 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. Ivett Leyva 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.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - Direct Numerical Simulations (DNS) were carried out in order to investigate the laminar-turbulent transition process on a flat plate boundary layer at Mach 6. Of particular interest is the nonlinear regime and whether any of the classical nonlinear breakdown mechanisms (fundamental resonance, subharmonic resonance, oblique breakdown) are relevant in the case of a flat plate. The conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University were used for the simulations. In order to investigate the relevant breakdown mechanism, the flow is perturbed with a short-duration pulse through a small blowing and suction hole at the wall. The resulting three-dimensional wave packets contain a wide range of frequencies and wavenumbers. The development of the wave packet as it propagates through the computational domain is explored with respect to the linear and the nonlinear regime by forcing with different initial disturbance amplitudes. In addition, the effect of forcing hole dimensions on the initial development of the wave packet downstream of the forcing location was explored.
AB - Direct Numerical Simulations (DNS) were carried out in order to investigate the laminar-turbulent transition process on a flat plate boundary layer at Mach 6. Of particular interest is the nonlinear regime and whether any of the classical nonlinear breakdown mechanisms (fundamental resonance, subharmonic resonance, oblique breakdown) are relevant in the case of a flat plate. The conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University were used for the simulations. In order to investigate the relevant breakdown mechanism, the flow is perturbed with a short-duration pulse through a small blowing and suction hole at the wall. The resulting three-dimensional wave packets contain a wide range of frequencies and wavenumbers. The development of the wave packet as it propagates through the computational domain is explored with respect to the linear and the nonlinear regime by forcing with different initial disturbance amplitudes. In addition, the effect of forcing hole dimensions on the initial development of the wave packet downstream of the forcing location was explored.
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U2 - 10.2514/6.2020-0586
DO - 10.2514/6.2020-0586
M3 - Conference contribution
AN - SCOPUS:85091946231
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
SP - 1
EP - 17
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -