Please use this identifier to cite or link to this item:
http://hdl.handle.net/10397/94148
DC Field | Value | Language |
---|---|---|
dc.contributor | Interdisciplinary Division of Aeronautical and Aviation Engineering | en_US |
dc.creator | Gu, S | en_US |
dc.creator | Olivier, H | en_US |
dc.creator | Wen, CY | en_US |
dc.creator | Hao, J | en_US |
dc.creator | Wang, Q | en_US |
dc.date.accessioned | 2022-08-11T01:07:26Z | - |
dc.date.available | 2022-08-11T01:07:26Z | - |
dc.identifier.issn | 1070-6631 | en_US |
dc.identifier.uri | http://hdl.handle.net/10397/94148 | - |
dc.language.iso | en | en_US |
dc.publisher | American Institute of Physics | en_US |
dc.rights | © 2022 Author(s). | en_US |
dc.rights | This article may be downloaded for personal use only. Any other use requires prior permission of the author and AIP Publishing. This article appeared in Sangdi Gu (顾桑迪), Herbert Olivier, Chih-Yung Wen (温志湧), Jiaao Hao (郝佳傲), and Qiu Wang (汪球), "Characterization of reflected shock tunnel air conditions using a simple method", Physics of Fluids 34, 056103 (2022) and may be found at https://dx.doi.org/10.1063/5.0089120. | en_US |
dc.title | Characterization of reflected shock tunnel air conditions using a simple method | en_US |
dc.type | Journal/Magazine Article | en_US |
dc.identifier.volume | 34 | en_US |
dc.identifier.issue | 5 | en_US |
dc.identifier.doi | 10.1063/5.0089120 | en_US |
dcterms.abstract | A new method to characterize air test conditions in hypersonic impulse facilities is introduced. It is a hybrid experimental-computational rebuilding method that uses the Fay-Riddell correlation with corrections based on thermochemical nonequilibrium computational fluid dynamic results. Its benefits include simplicity and time-resolution, and using this method, a unique characterization can be made for each individual experimental run. Simplicity is achieved by avoiding the use of any optical techniques and overly expensive numerical computations while still maintaining accuracy. Without making any assumptions to relate the reservoir conditions to the nozzle exit conditions, the work done characterizing four test conditions in a reflected shock tunnel is presented. In this type of facility, shock compression is used to produce an appropriate reservoir, which is then expanded through a nozzle to produce hypersonic flow. Particular focus is given to the nozzle exit total enthalpy where a comparison is made with the reservoir enthalpy obtained using the measured shock speed and pressure in the shock tube. Good agreement is observed in all cases providing validation of the new approach. Additionally, static pressure measurements showed clearly that conditions III and IV have a thermochemical state which likely froze shortly after the nozzle throat. Also, the nozzle flow is shown to be almost isentropic. Due to the simplicity of the current method, it can be easily implemented in existing facilities to provide an additional independent estimate alongside existing results. | en_US |
dcterms.accessRights | open access | en_US |
dcterms.bibliographicCitation | Physics of fluids, May 2022, v. 34, no. 5, 056103 | en_US |
dcterms.isPartOf | Physics of fluids | en_US |
dcterms.issued | 2022-05 | - |
dc.identifier.scopus | 2-s2.0-85130521952 | - |
dc.identifier.eissn | 1089-7666 | en_US |
dc.identifier.artn | 056103 | en_US |
dc.description.validate | 202208 bcrc | en_US |
dc.description.oa | Accepted Manuscript | en_US |
dc.identifier.FolderNumber | a1623 | - |
dc.identifier.SubFormID | 45637 | - |
dc.description.fundingSource | Self-funded | en_US |
dc.description.pubStatus | Published | en_US |
Appears in Collections: | Journal/Magazine Article |
Files in This Item:
File | Description | Size | Format | |
---|---|---|---|---|
Gu_Shock_Tunnel_Air.pdf | Pre-Published version | 3.54 MB | Adobe PDF | View/Open |
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