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Preliminary numerical study of three-temperature model investigation of hypersonic oxygen flow under rotational nonequilibrium

Preliminary numerical study of three-temperature model investigation of hypersonic oxygen flow... The effect of rotational nonequilibrium on the macroscopic parameters of the flow behind a normal shock wave in oxygen gas flow has been examined. The electron thermal equilibrium was taken into account where the electron temperature was equal to the vibrational temperature according to Park’s assumption. Therefore, only the effect of rotational nonequilibrium on the translational and vibrational temperature was analyzed. Rotational and vibrational relaxation time for the O2-O2 and O2-O collisions proposed recently by Andrienko and Boyd are used. Also, the O2 dissociation rates proposed by Kim and Park are used. The results obtained with the three-temperature model well reproduce the data obtained in shock tube for the shock velocity of 4.44 km/s. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

Preliminary numerical study of three-temperature model investigation of hypersonic oxygen flow under rotational nonequilibrium

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Publisher
Springer Journals
Copyright
Copyright © Y. Ghezali, R. Haoui, and A. Chpoun 2020
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/S0869864320060086
Publisher site
See Article on Publisher Site

Abstract

The effect of rotational nonequilibrium on the macroscopic parameters of the flow behind a normal shock wave in oxygen gas flow has been examined. The electron thermal equilibrium was taken into account where the electron temperature was equal to the vibrational temperature according to Park’s assumption. Therefore, only the effect of rotational nonequilibrium on the translational and vibrational temperature was analyzed. Rotational and vibrational relaxation time for the O2-O2 and O2-O collisions proposed recently by Andrienko and Boyd are used. Also, the O2 dissociation rates proposed by Kim and Park are used. The results obtained with the three-temperature model well reproduce the data obtained in shock tube for the shock velocity of 4.44 km/s.

Journal

Thermophysics and AeromechanicsSpringer Journals

Published: Mar 5, 2021

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