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Ionizing argon boundary layers. Part 2. Shock-tube side-wall boundary-layer flows

Published online by Cambridge University Press:  19 April 2006

W. S. Liu
Affiliation:
Institute for Aerospace Studies, University of Toronto, Ontario, Canada M3H 5T6 Present address: Thermalhydraulics Research Branch, Whiteshell Nuclear Research Establishment, AECL, Pinawa, Manitoba, Canada R0E 1LO.
I. I. Glass
Affiliation:
Institute for Aerospace Studies, University of Toronto, Ontario, Canada M3H 5T6

Abstract

A combined experimental and theoretical investigation was conducted on the shock-tube side-wall ionizing boundary-layer induced by a shock wave moving into argon. The dual-wavelength interferometric boundary-layer data were obtained by using a 23 cm diameter Mach—Zehnder interferometer with the 10 × 18 cm Hypervelocity Shock Tube at initial shock Mach numbers of 13 and 16, an initial pressure of 5 torr and a temperature of 300° K. The plasma density and electron number density in the boundary layer were measured and compared with numerical profiles obtained by using an implicit finite-difference scheme for a two-temperature, chemical non-equilibrium, laminar boundary-layer flow in ionizing argon. The analysis included the variations of transport properties based on elastic-scattering cross-sections, effects of chemical reactions, radiation-energy losses and electron-sheath wall boundary conditions. Considering the difficulties involved in such complex plasma flows, satisfactory agreement was obtained between the analyses and experiments. A comparison was made with the flat-plate case and despite the very different velocity boundary conditions at the wall for the two flows the experimental data appear to be quite similar. The experimental bump in the profile of electron number density which was found in the flat-plate case was not found in the side-wall case. Comparisons and discussions of the results for the different types of boundary layer are presented, including a comparison between experimentally derived and analytical plasma-temperature profiles.

Type
Research Article
Copyright
© 1979 Cambridge University Press

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References

Boyer, A. G. 1965 Inst. Aerospace Stud., Univ. Toronto. Rep. UTIAS 99.
Bredfeldt, H. R., Scharfman, W. E., Guthart, H. & Morita, T. 1967 A.I.A.A. J. 5, 91.
Brimelow, P. I. 1974 Inst. Aerospace Stud., Univ. Toronto Tech. Note UTIAS 187.
Bristow, M. P. F. 1971 Inst. Aerospace Stud. Univ. Toronto Rep. UTIAS 158.
Brown, R. T. & Mitchner, M. 1971 Phys. Fluids 14, 933.
Enomoto, Y. 1973 J. Phys. Soc. Japan 35, 1228.
Glass, I. I. & Liu, W. S. 1978 J. Fluid Mech. 84, 55.
Glass, I. I., Liu, W. S. & Taug, F. C. 1977 Can. J. Phys. 56, 1269.
Honma, H. & Komuro, H. 1976 A.I.A.A. J. 14, 981.
Hutten Mansfeld, A. C. B. 1976 Ph.D. thesis, Eindhoven University of Technology.
Kns, S. P. 1968 J. Plasma Phys. 2, 207.
Kuiper, R. 1968 Stanford Univ. Sudaar Rep. no. 353.
Liu, W. S., Whitten, B. T. & Glass, I. I. 1978 J. Fluid Mech. 87, 609.
Mirels, H. 1966 Phys. Fluids 9, 1907.
Takano, Y. & Akamatsu, T. 1975 J. Japan Soc. Aero. Space Sci. 23, 126.
Tano, F. C. 1977 Inst. Aerospace Stud. Univ. Toronto Rep. UTIAS 212.
Tseng, R. C. & Talbot, L. 1971 A.I.A.A. J. 9, 1365.
Whitten, B. T. 1978 Inst. Aerospace Stud. Univ. Toronto Rep. UTIAS.