Conference item
Aerodynamic effects and heat flux augmentation of a transpiration cooled hypersonic sharp leading edge
- Abstract:
- This paper presents numerical results investigating the aerodynamic and aerothermal effects of mass injection applied to hypersonic sharp leading edges, in the context of active thermal protection systems. A numerical study was carried out using Eilmer to investigate the coupling of leading edge radius and mass injection on heat flux and drag augmentations. Radii from 1 mm to 25 mm were considered at blowing parameters from 0.0 to 1.5 on 2D planar leading edge at a fixed trajectory point. Drag was found to barely change with mass injection, whereas heat flux was found to significantly reduce at the leading edge. The leading edge heat flux distribution could be collapsed, and therefore predicted, straightforwardly. Film cooling predictive methods in literature for other mass injection scenarios were found to collapse the heat flux and concentration comfortably with empirical modifications.
- Publication status:
- Published
- Peer review status:
- Peer reviewed
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Access Document
- Files:
-
-
(Preview, Accepted manuscript, pdf, 3.8MB, Terms of use)
-
- Publisher copy:
- 10.2514/6.2023-0437
Authors
- Publisher:
- American Institute of Aeronautics and Astronautics.
- Host title:
- AIAA SCITECH 2023 Forum
- Article number:
- AIAA 2023-0437
- Series:
- AIAA SciTech Forum
- Publication date:
- 2023-01-19
- Acceptance date:
- 2023-01-23
- Event title:
- AIAA SciTech 2023
- Event location:
- National Harbour, MD, USA
- Event website:
- https://www.aiaa.org/SciTech/utility/past-forums#2023
- Event start date:
- 2023-01-23
- Event end date:
- 2023-01-27
- DOI:
- Commissioning body:
- American Institute of Aeronautics and Astronautics
- EISBN:
- 9781624106996
- Language:
-
English
- Keywords:
- Pubs id:
-
1319730
- Local pid:
-
pubs:1319730
- Deposit date:
-
2023-01-11
- ARK identifier:
Terms of use
- Copyright holder:
- American Institute of Aeronautics and Astronautics, Inc.
- Copyright date:
- 2023
- Rights statement:
- Copyright © 2023 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
- Notes:
- This is the accepted manuscript version of the paper. The final version is available online from American Institute of Aeronautics and Astronautics at: https://doi.org/10.2514/6.2023-0437
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