Stagnation temperature measurements in the USQ hypersonic wind tunnel
Paper
Paper/Presentation Title | Stagnation temperature measurements in the USQ hypersonic wind tunnel |
---|---|
Presentation Type | Paper |
Authors | Widodo, A. S. (Author) and Buttsworth, D. R. (Author) |
Editors | Mallinson, G. D. and Cater, J. E. |
Journal or Proceedings Title | Proceedings of the 17th Australiasian Fluid Mechanics Conference (AFMC 2010) |
ERA Conference ID | 42494 |
Journal Citation | 248 (4778), pp. 840-844 |
Number of Pages | 5 |
Year | 2010 |
Place of Publication | Auckland, New Zealand |
ISBN | 9781617829130 |
Digital Object Identifier (DOI) | https://doi.org/10.1038/190778a0 |
Web Address (URL) of Paper | http://www.17afmc.com/17afmc/ |
Conference/Event | 17th Australasian Fluid Mechanics Conference (AFMC 2010) |
Australasian Fluid Mechanics Conference | |
Event Details | Australasian Fluid Mechanics Conference Rank A A A A A A A A |
Event Details | 17th Australasian Fluid Mechanics Conference (AFMC 2010) Parent Australasian Fluid Mechanics Conference Delivery In person Event Date 05 to end of 09 Dec 2010 Event Location Auckland, New Zealand |
Abstract | A thermocouple probe with a heated shield has been used to measure stagnation temperature at the nozzle exit of the University of Southern Queensland hypersonic wind tunnel. The thermocouple probe consisted of a welded junction T-type thermocouple mounted within a heated tube with a vent hole downstream of the junction. Pressure transducers within the barrel of the wind tunnel have also been used to obtain the pressure history during the free piston compression process. The pressure measurements have been used to provide a theoretical value for the flow stagnation temperature for direct comparison with the thermocouple measurements. Assuming isentropic compression of the test gas, the flow stagnation temperature would be about 571 K for the current operating condition. After applying a response-time correction for the thermocouple signals, a stagnation temperature value of about 495 K was obtained from the measurements. The measured stagnation temperature of the test gas is somewhat lower than the isentropic value because of heat loss from the test gas to the barrel during the test gas compression and discharge process. |
Keywords | hypersonic flow; temperature measurement |
ANZSRC Field of Research 2020 | 400199. Aerospace engineering not elsewhere classified |
401799. Mechanical engineering not elsewhere classified | |
400106. Hypersonic propulsion and hypersonic aerothermodynamics | |
Public Notes | No evidence of copyright restrictions preventing deposit. |
Byline Affiliations | Faculty of Engineering and Surveying |
University of Oxford, United Kingdom | |
Institution of Origin | University of Southern Queensland |
https://research.usq.edu.au/item/q080x/stagnation-temperature-measurements-in-the-usq-hypersonic-wind-tunnel
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