Particulate induced-transition provides a possible path to turbulence for high-speed vehicles traveling through the atmosphere. Particulates impinging onto the surface of high-speed vehicles can trigger a wavepacket inside the boundary-layer which, based on the flow and particulate conditions, subsequently can grow substantially and ultimately transition the flow to turbulence. Modeling this transition scenario on a computer is highly challenging due to the large range of scales relevant to the problem including micron-size particulates and wavepackets with a streamwise extent of several boundary-layer thicknesses. The main objective of this paper is to introduce a high-fidelity simulation approach to model particulate-flow interactions for hypersonic transitional boundary-layers employing an established immersed boundary method. This high-fidelity simulation approach will be compared against the particle-source-in-cell method which is commonly used to model particulate-flow interactions. The particulate-laden flow simulations are conducted for a M=5.35 flat plate boundary layer flow considering different particulate impingement scenarios, e.g., for different impingement locations (upstream of neutral curve and inside unstable flow region) and impingement angles.
|Title of host publication||AIAA Scitech 2020 Forum|
|State||Published - 2020|
|Event||AIAA Scitech Forum, 2020 - Orlando, United States|
Duration: Jan 6 2020 → Jan 10 2020
|Name||AIAA Scitech 2020 Forum|
|Conference||AIAA Scitech Forum, 2020|
|Period||1/6/20 → 1/10/20|
Bibliographical noteFunding Information:
This research is part of the Blue Waters sustained-petascale computing project, which is supported by the National Science Foundation (awards OCI-0725070 and ACI-1238993) and the state of Illinois. Blue Waters is a joint effort of the University of Illinois at Urbana-Champaign and its National Center for Supercomputing Applications. Some funding support was provided by the Office of Naval Research under contract N00014-19-1-2223 with Dr. Eric Marineau as program manager is gratefully acknowledged. Moreover, the authors want to thank Dr. Anatoli Tumin at University of Arizona for many fruitful discussions on this topic. Finally, the authors are very grateful to Anthony Haas at University of Arizona for providing LST results which greatly helped to provide a better understanding of the simulation results.
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ASJC Scopus subject areas
- Aerospace Engineering