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Flow in shock tubes with area change at the diaphragm section

Published online by Cambridge University Press:  28 March 2006

R. A. Alpher
Affiliation:
General Electric Research Laboratory, Schenectady, New York
D. R. White
Affiliation:
General Electric Research Laboratory, Schenectady, New York

Abstract

This paper describes theoretical and experimental studies of the effects on shock tube flows of a monotonic convergence at the diaphragm section. Systematic flow equations are developed for tubes of uniform bore and tubes having either a monotonic convergence or a convergence-divergence in the diaphragm section. Except across the shock front itself, isentropic processes and ideal-gas behaviour have been assumed. Simplified procedures are presented for predicting the ideal-flow parameters over a wide range of operating conditions, as well as for comparing straight and convergent tubes. Such comparisons made by other investigators are found to be incomplete or in error. The experiments described utilize a very simple device for altering the diaphragm section convergence and a multi-station measurement of shock velocity. The expected effect of convergence is verified over a wide range of Mach numbers. Even at Mach numbers where the processes of shock formation can no longer be ignored, it is found that the relative performance between a uniform and convergent tube is preserved.

Type
Research Article
Copyright
© 1958 Cambridge University Press

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Footnotes

A preliminary account of this work was given at the 1957 Annual Meeting of the American Physical Society in New York City.

References

Alpher, R. A. 1957 The Saha equation and the adiabatic exponent in shock wave calculations, J. Fluid Mech. 2, 123.Google Scholar
Alpher, R. A. & White, D. R. 1957 Ideal theory of shock tubes with area change near diaphragm, General Electric Research Laboratory, Schenectady, New York, Report no. 57-RL-1664.Google Scholar
Bannister, F. K. & Mucklow, G. F. 1948 Wave action following sudden release of compressed gas from a cylinder, Proc. Instn Mech. Engrs. 159, 269.Google Scholar
Döring, W. 1949 Die Geschwindigkeit und Struktur von intensiven Stosswellen in Gasen, Ann. d. Phys. 6, 133.Google Scholar
Hooker, W. J. & White, D. R. 1955 Design considerations for shock tubes generating hypersonic flow (M > 6), General Electric Research Laboratory, Schenectady, New York, Chemistry Research Department Mem. Rep. no. C-55-120.Google Scholar
Liepmann, H. W. & Puckett, A. E. 1947 Introduction to Aerodynamics of a Compressible Fluid. New York: Wiley.
Lighthill, M. J. 1957 Dynamics of a dissociating gas, Part I, equilibrium flow, J. Fluid Mech. 2, 1.Google Scholar
Lukasiewicz, L. 1952 Shock tube theory and application, National Aeronatical Establishment, Ottawa, Report no. 15.Google Scholar
Rabinowicz, J., Jessey, M. E. & Bartsch, C. A. 1956 Resistance thermometer for transient high-temperature studies, J. Appl. Phys. 27, 97.Google Scholar
Resler, E. L., Lin, S. C. & Kantrowitz, A. 1952 The production of high temperature gases in shock tubes, J. Appl. Phys. 23, 1390.Google Scholar
Wallace, F. J. & Mitchell, R. W. S. 1953 Wave action following the sudden release of air through an engine port system, Proc. Instn Mech. Engrs. (B) 1B, 8 & 343.Google Scholar
Wallace, F. J. and Nassif, M. H. 1954 Air flow in naturally aspirated two stroke engines, Proc. Instn Mech. Engrs. 168, 515.Google Scholar
Yoler, Y. A. 1954 Hypersonic shock tube, California Institute of Technology, Guggenheim Aeronautical Laboratory, Hypersonic Wind Tunnel Project, Mem. no. 18.Google Scholar