Free-Flight of a Propelled Model in a High-Speed Ground-Test Facility
Paper
McQuellin, Liam P., Noller, Lachlan J. and Buttsworth, David R.. 2024. "Free-Flight of a Propelled Model in a High-Speed Ground-Test Facility." AIAA SciTech Forum 2024. Orlando, FL, United States 08 - 12 Jan 2024 United States. https://doi.org/10.2514/6.2024-2889
| Paper/Presentation Title | Free-Flight of a Propelled Model in a High-Speed Ground-Test Facility |
|---|---|
| Presentation Type | Paper |
| Authors | McQuellin, Liam P., Noller, Lachlan J. and Buttsworth, David R. |
| Journal or Proceedings Title | Proceedings of AIAA SciTech Forum (2024) |
| Number of Pages | 20 |
| Year | 2024 |
| Place of Publication | United States |
| ISBN | 9781624107115 |
| Digital Object Identifier (DOI) | https://doi.org/10.2514/6.2024-2889 |
| Web Address (URL) of Paper | https://arc.aiaa.org/doi/10.2514/6.2024-2889 |
| Web Address (URL) of Conference Proceedings | https://arc.aiaa.org/doi/book/10.2514/MSCITECH24 |
| Conference/Event | AIAA SciTech Forum 2024 |
| Event Details | AIAA SciTech Forum 2024 Event Date 08 to end of 12 Jan 2024 Event Location Orlando, FL, United States |
| Abstract | High-speed vehicle aerodynamics, flight dynamics, and wake signatures can be profoundly influenced by propulsive effects. Free-flight model techniques in high speed ground-test facilities provide opportunities to investigate such matters free of sting supports that can alter base-flow characteristics, but propelled free-flight models have not previously been demonstrated. A technique for launching propelled free-flight rocket models is introduced. The rocket model was pneumatically launched and was propelled upstream by a cold-gas thruster with a nozzle exit area ratio of 25. On-board accelerometer data are typically within ±3 standard deviations of the mean acceleration from optical tracking data at each moment in time and both methods demonstrate that net thrust was achieved for a period of 75 ms in the Mach 4.5 stream. On-board cold-gas plenum pressure measurements provide a basis for simulation of the thrust from the propulsion system and such simulations compare favorably with measurements obtained from other experiments where models were launched into the low-pressure quiescent test section environment. Flow visualization reveals the presence of flow separation along the rocket body downstream of the nose-cone region, which appears to be sustained by the influence from the pneumatic launching system propagating upstream via the model wake. The higher pressures in the base flow region associated with observed separated flow reduce the net drag relative to the expected free-flight value in the Mach 4.5 flow. In future work, the pneumatic launch system can be re-designed to reduce its frontal area; the launch system could also be designed to translate downstream just after model release in an effort to minimize the potential interference effect. © 2024 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. |
| Contains Sensitive Content | Does not contain sensitive content |
| ANZSRC Field of Research 2020 | 400199. Aerospace engineering not elsewhere classified |
| Public Notes | Files associated with this item cannot be displayed due to copyright restrictions. |
| Byline Affiliations | University of New South Wales |
| University of Southern Queensland |
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https://research.usq.edu.au/item/z861q/free-flight-of-a-propelled-model-in-a-high-speed-ground-test-facility
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