Abstract
The transition of a laminar to turbulent boundary layer plays an important role in the design of hypersonic vehicles. This is primarily because a turbulent boundary layer produces significantly higher heat transfer rates than a laminar boundary layer. Therefore, the Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Turbulence (BoLT-2) flight experiment to improve understanding and prediction of hypersonic boundary layer turbulence. This paper presents results for the 25% subscale BoLT-2 geometry using US3D to simulate the steady state flow field and the ability of current RANS models to approximate aeroheating using a trip-induced turbulence modeling approach. Additionally, a random forcing approach is investigated by varying the forcing amplitude to simulate natural boundary layer transition leading to breakdown. The results were compared to experiments performed on a 25% subscale model carried out in the Mach 6 Quiet Tunnel (M6QT) at Texas A&M University.
| Original language | English (US) |
|---|---|
| Title of host publication | AIAA Scitech 2021 Forum |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Pages | 1-14 |
| Number of pages | 14 |
| ISBN (Print) | 9781624106095 |
| State | Published - 2021 |
| Externally published | Yes |
| Event | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online Duration: Jan 11 2021 → Jan 15 2021 |
Publication series
| Name | AIAA Scitech 2021 Forum |
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Conference
| Conference | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 |
|---|---|
| City | Virtual, Online |
| Period | 1/11/21 → 1/15/21 |
Bibliographical note
Funding Information:This work was supported by the DoD HPCMP Hypersonic Vehicle Simulation Institute, the Collaborative Center for Aerospace Sciences, and the Air Force Office of Scientific Research (AFOSR) under grant FA9550-18-1-0009. 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 AFOSR or the U.S Government. The authors would like to thank Heather Kostak for providing experimental data, Daniel Mullen for providing initial stability analysis, and John Thome for providing helpful collaboration and discussions.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.