Aerothermoelastic Response of a Radiatively Heated Compliant Panel in Mach 6 Flow
Paper
Tuten, Zacharia, Dooner, Dylan D., Neely, Andrew J. and Buttsworth, David. 2025. "Aerothermoelastic Response of a Radiatively Heated Compliant Panel in Mach 6 Flow." AIAA SciTech Forum 2025. Orlando, FL, United States 06 - 10 Jan 2025 United States. https://doi.org/10.2514/6.2025-2454
Paper/Presentation Title | Aerothermoelastic Response of a Radiatively Heated Compliant Panel in Mach 6 Flow |
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Presentation Type | Paper |
Authors | Tuten, Zacharia, Dooner, Dylan D., Neely, Andrew J. and Buttsworth, David |
Year | 2025 |
Place of Publication | United States |
ISBN | 9781624107238 |
Digital Object Identifier (DOI) | https://doi.org/10.2514/6.2025-2454 |
Web Address (URL) of Paper | https://arc.aiaa.org/doi/abs/10.2514/6.2025-2454 |
Web Address (URL) of Conference Proceedings | https://arc.aiaa.org/doi/book/10.2514/MSCITECH25 |
Conference/Event | AIAA SciTech Forum 2025 |
Event Details | AIAA SciTech Forum 2025 Delivery In person Event Date 06 to end of 10 Jan 2025 Event Location Orlando, FL, United States |
Abstract | Hypersonic aerothermoelastic data are needed to investigate fundamental physics and support the validation of numerical models. To this end, a novel experimental model, HyRAD, was developed and tested in TUSQ at Mach 5.9 with ∼220 ms flow time. On the model, a clamped-free-clamped-free compliant 120 mm x 60 mm x 1 mm AL6061-T6 panel was positioned at 0° and 5° inclination at room and elevated temperatures (maximum of 533 K) with the intention of measuring modal frequency shifts caused by temperature change. The panel was pre-heated radiatively by a thermo-resistively heated sheet of carbon-carbon. Thermal stress was prevented by allowing the panel to expand during heating, followed by the engagement of a remotely-actuated clamp to make the structure rigid. Panel temperatures were simulated and verified using infrared camera measurements. Deflections below 50 µm were resolved with a laser profilometer, schlieren imaging, and digital image correlation using in-house software. Thermally-induced frequency shifts for minimally-loaded bending modes (post flow and at 0° inclination) agreed with simulation. Thermally-induced frequency shifts were smaller at 5° inclination during flow. Torsional mode frequency shifts were consistently smaller than simulated. |
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 New South Wales |
University of Southern Queensland |
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https://research.usq.edu.au/item/zx209/aerothermoelastic-response-of-a-radiatively-heated-compliant-panel-in-mach-6-flow
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