Modelling the complete operation of a free-piston shock tunnel for a low enthalpy condition

McGilvray, M., Dann, A. G. and Jacobs, P. A. (2013) Modelling the complete operation of a free-piston shock tunnel for a low enthalpy condition. Shock Waves, 23 4: 399-406. doi:10.1007/s00193-013-0437-8

Author McGilvray, M.
Dann, A. G.
Jacobs, P. A.
Title Modelling the complete operation of a free-piston shock tunnel for a low enthalpy condition
Journal name Shock Waves   Check publisher's open access policy
ISSN 0938-1287
Publication date 2013-07
Year available 2013
Sub-type Article (original research)
DOI 10.1007/s00193-013-0437-8
Open Access Status
Volume 23
Issue 4
Start page 399
End page 406
Total pages 8
Place of publication Heidelberg, Germany
Publisher Springer
Collection year 2014
Language eng
Abstract Only a limited number of free-stream flow properties can be measured in hypersonic impulse facilities at the nozzle exit. This poses challenges for experimenters when subsequently analysing experimental data obtained from these facilities. Typically in a reflected shock tunnel, a simple analysis that requires small amounts of computational resources is used to calculate quasi-steady gas properties. This simple analysis requires initial fill conditions and experimental measurements in analytical calculations of each major flow process, using forward coupling with minor corrections to include processes that are not directly modeled. However, this simplistic approach leads to an unknown level of discrepancy to the true flow properties. To explore the simple modelling techniques accuracy, this paper details the use of transient one and two-dimensional numerical simulations of a complete facility to obtain more refined free-stream flow properties from a free-piston reflected shock tunnel operating at low-enthalpy conditions. These calculations were verified by comparison to experimental data obtained from the facility. For the condition and facility investigated, the test conditions at nozzle exit produced with the simple modelling technique agree with the time and space averaged results from the complete facility calculations to within the accuracy of the experimental measurements.
Keyword Hypersonic flow
Shock tunnel
Transient flow
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2014 Collection
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