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 TypePaper
AuthorsNeely, Andrew J., Choudhury, Rishabh, Paukner, Daniel and Odam, Judy
Journal or Proceedings TitleProceedings of the 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (2011)
Article Number2011-2356
Year2011
PublisherAmerican Institute of Aeronautics and Astronautics
Place of PublicationUnited States
ISBN9781600869426
Digital Object Identifier (DOI)https://doi.org/10.2514/6.2011-2356
Web Address (URL) of Paperhttps://arc.aiaa.org/doi/abs/10.2514/6.2011-2356
Conference/Event17th 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.

KeywordsAerothermal heating; CFD simulations; Colour change; Conjugate heat transfer; Engineering development; Flight profiles; Risk reductions; Thermal paints
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FunderU.S. Air Force
Byline AffiliationsUniversity of New South Wales
Technical University of Munich, Germany
Department of Defence, Australia
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