Mach 6 and Mach 7 conditions in TUSQ at Reynolds numbers up to 30 million
Paper
Moran, Jeremy, Buttsworth, David R. and Noller, Lachlan. 2024. "Mach 6 and Mach 7 conditions in TUSQ at Reynolds numbers up to 30 million." AIAA Aviation Forum and ASCEND 2024. Las Vegas, United States 29 Jul - 02 Aug 2024 United States. https://doi.org/10.2514/6.2024-4197
Paper/Presentation Title | Mach 6 and Mach 7 conditions in TUSQ at Reynolds numbers up to 30 million |
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Presentation Type | Paper |
Authors | Moran, Jeremy, Buttsworth, David R. and Noller, Lachlan |
Journal or Proceedings Title | Proceedings of AIAA Aviation Forum and ASCEND 2024 |
Year | 2024 |
Place of Publication | United States |
ISBN | 9781624107160 |
Digital Object Identifier (DOI) | https://doi.org/10.2514/6.2024-4197 |
Web Address (URL) of Paper | https://arc.aiaa.org/doi/abs/10.2514/6.2024-4197 |
Web Address (URL) of Conference Proceedings | https://arc.aiaa.org/doi/book/10.2514/MAVAS24 |
Conference/Event | AIAA Aviation Forum and ASCEND 2024 |
Event Details | AIAA Aviation Forum and ASCEND 2024 Delivery In person Event Date 29 Jul 2024 to end of 02 Aug 2024 Event Location Las Vegas, United States |
Abstract | The TUSQ hypersonic wind tunnel at the University of Southern Queensland has been operational for almost 15 years and has most commonly been used for Mach 6 and Mach 7 experiments with stagnation pressures of 1.3 MPa or less. New operating conditions that increase the flow stagnation pressure up to 5.2 MPa and the achievable unit Reynolds numbers up to 30 × 106 m?1 have recently been demonstrated in the TUSQ facility. The primary development that has enabled the higher pressure conditions is the application of copper diaphragms at the Mach 6 and Mach 7 nozzle inlets; the geometric features of these diaphragms are detailed herein. Stagnation pressure histories for a range of flow conditions with the Mach 6 and Mach 7 nozzle are presented. For the Mach 6 nozzle at a stagnation pressure of 3.9 MPa (producing unit Reynolds number of 30 × 106 m?1 ), temporal variations in flow stagnation pressure of less than about ±4% are observed within the flow duration of approximately 220 ms; for the Mach 7 nozzle at a stagnation pressure of 5.2 MPa (producing unit Reynolds number of 25 × 106 m?1 ), variations of less than ±2% are observed within the flow duration of approximately 350 ms. © 2024, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. |
Contains Sensitive Content | Does not contain sensitive content |
ANZSRC Field of Research 2020 | 400199. Aerospace engineering not elsewhere classified |
Public Notes | There are no files associated with this item. |
Byline Affiliations | University of Southern Queensland |
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