Effect of non-equilibrium thermochemistry on Pitot pressure measurements in shock tunnels (or: Is 0.92 really the magic number?)

Article


Sopek, Tamara, Jacobs, Peter, Subiah, Suria-Devi, Collen, Peter and McGilvray, Matthew. 2024. "Effect of non-equilibrium thermochemistry on Pitot pressure measurements in shock tunnels (or: Is 0.92 really the magic number?)." Acta Astronautica. 223, pp. 249-261. https://doi.org/10.1016/j.actaastro.2024.07.008
Article Title

Effect of non-equilibrium thermochemistry on Pitot pressure measurements
in shock tunnels (or: Is 0.92 really the magic number?)

ERA Journal ID3572
Article CategoryArticle
AuthorsSopek, Tamara, Jacobs, Peter, Subiah, Suria-Devi, Collen, Peter and McGilvray, Matthew
Journal TitleActa Astronautica
Journal Citation223, pp. 249-261
Number of Pages13
Year2024
PublisherElsevier
Place of PublicationUnited Kingdom
ISSN0094-5765
1879-2030
Digital Object Identifier (DOI)https://doi.org/10.1016/j.actaastro.2024.07.008
Web Address (URL)https://www.sciencedirect.com/science/article/pii/S009457652400376X
Abstract

Pitot pressure is the most common measurement in high total enthalpy shock tunnels for test condition verification. Nozzle calculations using multi-temperature non-equilibrium thermochemistry are needed in conjunction with Pitot measurements to quantify freestream properties. Pitot pressure is typically matched by tuning the boundary layer transition location in these simulations. However, non-equilibrium thermochemistry effects on the Pitot probe are commonly ignored. A computational study was undertaken to estimate the effect of non-equilibrium thermochemistry on Pitot pressure and freestream conditions. The test flow was produced by a Mach 7 nozzle in a reflected shock tunnel for air at a relatively low total enthalpy of 2.67 MJ/kg. Three different thermochemical models (equilibrium, finite-rate chemistry and two-temperature thermochemistry) were employed to compute flow variables at the nozzle exit and Pitot probe. Pitot pressures from these simulations were compared against those obtained via experiments. The results show a departure from the commonly utilized đ¶ of 0.92 in the reduced Rayleigh-Pitot equation form for high Mach numbers. Additionally, calculations were done with a sweep of free-stream conditions and resulting in values for one- and twotemperature models to use in future shock tunnel studies. Overall, our results show that the influence of finite-rate thermochemistry should be taken into account, even at relatively low flow enthalpies.

KeywordsPitot pressure; Fluid mechanics; Hypersonics; Shock tunnel; Computational fluid dynamics
Contains Sensitive ContentDoes not contain sensitive content
ANZSRC Field of Research 2020400106. Hypersonic propulsion and hypersonic aerothermodynamics
400199. Aerospace engineering not elsewhere classified
401204. Computational methods in fluid flow, heat and mass transfer (incl. computational fluid dynamics)
Byline AffiliationsUniversity of Southern Queensland
University of Oxford, United Kingdom
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