Temperature and heat flux measurement on hot models in short-duration facilities
Article
Article Title | Temperature and heat flux measurement on hot models in short-duration facilities |
---|---|
ERA Journal ID | 5155 |
Article Category | Article |
Authors | Kraetzig, Benjamin (Author), Buttsworth, David R. (Author), Zander, Fabian (Author) and Loehle, Stefan (Author) |
Journal Title | Journal of Thermophysics and Heat Transfer |
Journal Citation | 29 (1), pp. 37-46 |
Number of Pages | 10 |
Year | 2014 |
Publisher | American Institute of Aeronautics and Astronautics |
Place of Publication | United States |
ISSN | 0887-8722 |
1533-6808 | |
Digital Object Identifier (DOI) | https://doi.org/10.2514/1.T4309 |
Web Address (URL) | http://arc.aiaa.org/doi/abs/10.2514/1.T4309 |
Abstract | An electrical preheating technique applied to a carbon-based model in an impulse facility has previously demonstrated surface temperatures around 2500 K, but the measurement of heat flux at such elevated surface temperatures was not previously achieved. A technique for fast-response surface temperature measurement of an electrically preheated carbon-phenolic model using an indium gallium arsenide detector with in situ calibration via a visible/near-infrared spectrometer is assessed through application in a short-duration cold-flow hypersonic wind tunnel. The method is reliable: the scatter in temperatures determined from successive acquisitions of the spectrometer data had a standard deviation of 3 K at a mean temperature of about 1500 K; the standard deviation of the Indium gallium arsenide detector results from the visible/near-infrared spectrometer data was 11 K at a temperature of about 1100 K after the termination of the hypersonic flow. The surface temperature history from the Indium gallium arsenide detector was analyzed using a one-dimensional transient heat conduction model to deduce the surface heat flux. Good agreement with an engineering correlation for stagnation point heat flux is demonstrated; however, uncertainties are large (±33%), as the thermal properties of the particular carbon-phenolic material were not available. The method is suitable for application in impulse facilities, but the effusivity (√pck) for the heat shield material will need to be accurately defined for reliable deduction of surface heat flux. |
Keywords | atmospheric temperature; carbon; gallium; gallium arsenide; heat conduction; heat shielding; hypersonic flow; Indium; spectrometers; statistics; surface properties; temperature measurement; wind tunnels; electrical preheating; engineering correlations; heat flux measurement; hypersonic wind tunnels; Indium gallium arsenide; stagnation point heat fluxes; surface temperatures; transient heat conduction |
ANZSRC Field of Research 2020 | 400106. Hypersonic propulsion and hypersonic aerothermodynamics |
Public Notes | Files associated with this item cannot be displayed due to copyright restrictions. |
Byline Affiliations | University of Stuttgart, Germany |
School of Mechanical and Electrical Engineering | |
University of Queensland | |
Institution of Origin | University of Southern Queensland |
Funding source | Australian Research Council (ARC) |
https://research.usq.edu.au/item/q2ww2/temperature-and-heat-flux-measurement-on-hot-models-in-short-duration-facilities
1674
total views6
total downloads2
views this month0
downloads this month