@inproceedings{7a6ab492d1d04b80b9a655cb37d47fbb,
title = "Numerical Investigation of Hypersonic Boundary-Layer Transition for the Ogive Cone of the STORT Experiments",
abstract = "Direct Numerical Simulations (DNS) were carried out for an ogive cone with a blunt nose-tip at Mach 7.0 in order to investigate the laminar-turbulent transition process with an emphasis on the dominant nonlinear mechanisms. The primary instability regime was investigated using Linear Stability Theory (LST) for Mach 5.3 conditions in addition to Mach 7.0 to investigate the effect of Mach number on linear amplification rates. The LST analysis indicates that both first and second mode waves are amplified albeit with small N-factors. The second mode has a wide range of amplified frequencies due to the rapid downstream increase of the boundary-layer thickness. A secondary instability study revealed that fundamental resonance resulted in larger N-factors of the secondary wave after resonance onset compared to subharmonic resonance for the M∞ = 7.0 case. Subsequent highly resolved {\textquoteleft}controlled{\textquoteright} fundamental breakdown simulations for the M∞ = 7.0 case exhibit typical structures associated with fundamental breakdown, including {\textquoteleft}primary{\textquoteright} and {\textquoteleft}secondary{\textquoteright} hot streak patterns that have been previously observed in experiments and DNS for a flared cone. A detailed analysis of the breakdown simulations confirmed that the {"}hot{"} streaks on the surface of the ogive geometry are generated by the same nonlinear mechanism as for the flared cone.",
author = "Meersman, {John A.} and Christoph Hader and Fasel, {Hermann F.}",
note = "Funding Information: This work was supported by AFOSR Grant FA9550-19-1-0208 with program manager Dr. Sarah Popkin. Computer time was provided by the U.S. 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. Funding Information: This work was supported by AFOSR Grant FA9550-19-1-0208 with program manager Dr. Sarah Popkin. Computer time was provided by the U.S. 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. The authors would like to acknowledge Dr. Ali G?lhan and Dr. Sebastian Willems at the DLR Cologne for providing geometries, flow conditions, and for fruitful discussions. Furthermore, we would like to acknowledge Anthony Haas for providing LST results. Publisher Copyright: {\textcopyright} 2022, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.; AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022 ; Conference date: 03-01-2022 Through 07-01-2022",
year = "2022",
doi = "10.2514/6.2022-0946",
language = "English (US)",
isbn = "9781624106316",
series = "AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "AIAA SciTech Forum 2022",
}