Measurement of Aerothermal Heating on HIFiRE-0
Paper
Neely, Andrew J., Choudhury, Rishabh, Paukner, Daniel and Odam, Judy. 2011. "Measurement of Aerothermal Heating on HIFiRE-0." 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (2011). United States 11 - 14 Apr 2011 United States. American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2011-2356
| Paper/Presentation Title | Measurement of Aerothermal Heating on HIFiRE-0 |
|---|---|
| Presentation Type | Paper |
| Authors | Neely, Andrew J., Choudhury, Rishabh, Paukner, Daniel and Odam, Judy |
| Journal or Proceedings Title | Proceedings of the 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (2011) |
| Article Number | 2011-2356 |
| Year | 2011 |
| Publisher | American Institute of Aeronautics and Astronautics |
| Place of Publication | United States |
| ISBN | 9781600869426 |
| Digital Object Identifier (DOI) | https://doi.org/10.2514/6.2011-2356 |
| Web Address (URL) of Paper | https://arc.aiaa.org/doi/abs/10.2514/6.2011-2356 |
| Conference/Event | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (2011) |
| Event Details | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (2011) Parent AIAA International Space Planes and Hypersonic Systems and Technologies Conference Delivery Online Event Date 11 to end of 14 Apr 2011 Event Location United States |
| Abstract | Patches of permanent-change thermal paint were flown on DSTO's HIFiRE-0 hypersonic test vehicle. HIFiRE-0 was used as an engineering development and risk reduction flight for the fundamental science payload, HIFiRE 1 and subsequent flights in the HIFiRE series. Permanent-change thermal paint was applied to sections of the stainless steel nose cone, both externally and internally and to the aluminium instrumentation can. These paints were applied as an initial test of their suitability to measure the distribution of heating for a highly transient flight profile. After post-flight recovery of the payload, regions of the applied thermal paint were still clearly visible and had undergone a noticeable colour change due to inflight heating. Transient CFD simulations of the ascent and descent of the vehicle through the atmosphere, which incorporated conjugate heat transfer provided reasonable predicts of the observed paint colour change in the region investigated. © 2011 by Andrew J. Neely. |
| Keywords | Aerothermal heating; CFD simulations; Colour change; Conjugate heat transfer; Engineering development; Flight profiles; Risk reductions; Thermal paints |
| Public Notes | There are no files associated with this item. |
| Funder | U.S. Air Force |
| Byline Affiliations | University of New South Wales |
| Technical University of Munich, Germany | |
| Department of Defence, Australia | |
| Library Services |
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