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Thermal conductivity of argon at high temperatures

Published online by Cambridge University Press:  28 March 2006

Morton Camac  and
Robert M. Feinberg
Morton Camac
Affiliation:
Avco-Everett Research Laboratory, Everett, Massachusetts
Robert M. Feinberg
Affiliation:
Avco-Everett Research Laboratory, Everett, Massachusetts
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Extract

An infra-red heat-transfer gauge was used in a shock tube for end-wall measurements of the convective heat transfer from argon behind the reflected shock. The thermal conductivity of neutral (un-ionized) argon was measured before the ionization-relaxation time, and was fitted with the power-law temperature dependence 4·2 × 10−5(T/300)0·76±0·03 cal/sec cm°K, where T is measured in °K, and ±0·03 refers to the probable error The free-stream temperature ranged from 20,000 to 75,000°K, corresponding to incident-shock velocities from 3 to 6mm/μsec. At later times, after the free stream established equilibrium ionization, the convective-heat-transfer rate remained the same as the initial rate with neutral argon. Theoretical predictions of Fay & Kemp (1965), assuming equilibrium-boundary-layer conditions, are 20–30% below the experimental values. Also reported in this paper are measurements of the ionization times behind the reflected shock, and these are in agreement with an extrapolation of the Petschek & Byron (1957) measurements behind the incident shock. There is a discussion of the large changes in the gas conditions behind the reflected shock due to the ionization process. The final equilibrium conditions are reached abruptly, as indicated by the continuum-radiation emission which becomes constant immediately after ionization relaxation.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 21 , Issue 4 , April 1965 , pp. 673 - 688
Copyright
Copyright © Cambridge University Press 1965

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References

Amdur, I. & Mason, E. A. 1958 Phys. Fluids, 1, 370.Google Scholar
Bershader, D. & Rutowski, R. W. 1961 ARS Paper, no. 1998–61.Google Scholar
Byron, S. & Rott, N. 1961 Proc. 1961 Heat-Transfer and Fluid-Mech. Inst., ed. Binder, R. C.et al. Stanford University Press.Google Scholar
Camac, M. & Feinberg, R. M. 1962 Rev. Sci. Instrum. 33, 964.Google Scholar
Camac, M. & Feinberg, R. M. 1963 Avco-Everett Res. Lab., Res. Rep. no. 168.Google Scholar
Camac, M. & Kemp, N. H. 1963 AIAA Paper, no. 63–460.Google Scholar
Camac, M. & Teare, J. D. 1964 Avco-Everett Res. Lab., Res. Rep., no. 183.Google Scholar
Fay, J. A. 1964 The High Temperature Aspects of Hypersonic Flow, p. 583, ed. Nelson, W. C.. London: Pergamon Press.CrossRefGoogle Scholar
Fay, J. A. & Kemp, N. H. 1965 J. Fluid Mech. 21, 659.Google Scholar
Goldsworthy, F. A. 1959 J. Fluid Mech. 5, 164.Google Scholar
Jukes, J. 1956 Master of Aeronautical Engineering Thesis, Cornell Univ.Google Scholar
Mies, F. H. 1962 J. Chem. Phys. 37, 1101.Google Scholar
Petschek, H. E. & Byron, S. 1957 Ann. Phys. 1, 270.Google Scholar
Petschek, H. E., Rose, P. H., Glick, H. S., Kane, A. & Kantrowitz, A. R. 1955 J. Appl. Phys. 26, 83.Google Scholar
Reilly, J. P. 1963 Master of Aeronautical Engineering Thesis, Mass. Inst. Tech.Google Scholar
Smiley, E. F. 1957 Ph.D. Thesis, The Catholic Univ. America.Google Scholar
Sturtevant, B. 1964 APS Bull. 9, 583.Google Scholar
Van der Noordaa, R. S. L. 1957 Master of Aeronautical Engineering Thesis, Cornell Univ.Google Scholar