TY - GEN
T1 - Direct numerical simulations of laminar-turbulent boundary-layer transition for a blunt cone at mach 6
AU - Hartman, Andrew B.
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 Office of Naval Research or the U. S. Government. We acknowledge the fruitful discussions with Dr. Eric Marineau, Dr. Stefan Wernz (Raytheon Technology), Dr. Stuart Laurence, Dr. Stefan Hein (DLR) John Meersman (CFD Laboratory, University of Arizona) and Anthony Haas (CFD Laboratory University of Arizona) who also carried out the LST calculations.
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 to investigate the laminar-turbulent transition for blunt (right) cones (7◦ half-angle) at zero angle of attack. Two cases with different Reynolds numbers based on the nose radius were investigated. Linear stability calculations were carried out employing a high-order compressible Navier-Stokes solver and using very small disturbance amplitudes in order to capture the linear (primary) instability characteristics. The results of the linear stability calculations were then used to determine which nonlinear mechanism may likely be relevant and to choose the forcing parameters (frequency and azimuthal wavenumber) for "controlled" transition simulations that may lead to the transition. In order to determine if the disturbance waves identified from the linear calculations may indeed be able to trigger nonlinear breakdown, the disturbances were introduced in the entropy layer at high amplitudes.
AB - Direct Numerical Simulations (DNS) were carried out to investigate the laminar-turbulent transition for blunt (right) cones (7◦ half-angle) at zero angle of attack. Two cases with different Reynolds numbers based on the nose radius were investigated. Linear stability calculations were carried out employing a high-order compressible Navier-Stokes solver and using very small disturbance amplitudes in order to capture the linear (primary) instability characteristics. The results of the linear stability calculations were then used to determine which nonlinear mechanism may likely be relevant and to choose the forcing parameters (frequency and azimuthal wavenumber) for "controlled" transition simulations that may lead to the transition. In order to determine if the disturbance waves identified from the linear calculations may indeed be able to trigger nonlinear breakdown, the disturbances were introduced in the entropy layer at high amplitudes.
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M3 - Conference contribution
AN - SCOPUS:85100315432
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 13
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 -