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Experimentally Determined Structure of the Shock Reflection Process in Ionizing Xenon

Smith, Jerome A. (1968) Experimentally Determined Structure of the Shock Reflection Process in Ionizing Xenon. Physics of Fluids, 11 (10). pp. 2150-2161. ISSN 1070-6631. doi:10.1063/1.1691797.

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The results of an experimental investigation of the reflection of strong shocks in xenon from the end wall of a shock tube are presented. The reflection of the incident shock structure, consisting of a frozen shock front, a region of relatively uniform frozen flow, and an ionization front, was observed with a fast‐rise (0.3 μsec) pressure gauge mounted in the shock‐tube end wall. The incident shock Mach number was varied from 11‐20, and the initial pressure was varied from 0.1‐1.5mmHg. The interaction between the reflecting shock and the ionizing gas in the incident shock structure produces a complicated series of shock and rarefaction waves; those waves that propagate back to the end wall were observed with the pressure gauge. A simple model which includes the gross features of the shock reflection process is used to calculate end wall pressures. The calculated pressures agree well with the experimental observations. In addition, ionization relaxation times for xenon behind the incident and reflected shocks are presented. The relaxation time data yield a better understanding of the ionization relaxation process in monatomic gases and provide an estimate for the electron‐atom, inelastic cross section for xenon.

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Additional Information:© 1968 American Institute of Physics. (Received 20 December 1967; final manuscript received 6 June 1968) The author would like to express his sincere appreciation to Professor Anatol Roshko for his many helpful discussions in the course of this investigation and in writing this paper. Discussions with Professor H. W. Liepmann aided in the completion of this work, and his assistance is gratefully acknowledged. Special thanks go to Dr. Donald Baganoff for his patient instruction in the construction and use of the pressure gauge. The work in the Graduate Aeronautical Laboratories, California Institute of Technology 6-in. shock tube was supported by the National Aeronautics and Space Administration under Grant NsG 40-60.
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NASANsG 40-60
Issue or Number:10
Record Number:CaltechAUTHORS:20180529-164253185
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:86697
Deposited By: George Porter
Deposited On:30 May 2018 15:08
Last Modified:15 Nov 2021 20:41

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