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Behaviour of small regions of different gases carried in accelerated gas flows

Published online by Cambridge University Press:  28 March 2006

George Rudinger
Affiliation:
Cornell Aeronautical Laboratory, Buffalo, New York
Lowell M. Somers
Affiliation:
Cornell Aeronautical Laboratory, Buffalo, New York

Abstract

Small regions in a flow where the density is different from that of the surrounding gas do not exactly follow accelerated motions of the latter, but move faster or slower depending on whether their density is smaller or larger than that of the main flow. This behaviour cannot be quantitatively explained by treating a gas ‘bubble’ as a hypothetical solid particle of the same density, because a gas bubble cannot move relative to the surrounding gas without being transformed into a vortex which absorbs part of the energy of the relative motion.

To illustrate the acceleration effect, the flow velocity behind known pressure waves in a shock tube is compared with the observed velocity of a bubble produced by a spark discharge. The displacement of such a bubble by a wave exceeds that of a flow element by more than 20%, but the bubble density is not known. If the spark discharge is replaced by a small jet of another gas, a pressure wave cuts off a section of this jet which then represents a bubble of known density.

A theory is developed which permits computing the response of such bubbles to accelerations. The ratio of the bubble velocity to the velocity of the surrounding gas depends on the density ratio for the two gases and on the shape of the bubble, but not on the acceleration. Experimental results with H2, He, and SF6 bubbles in air, accelerated by shock waves of various strength, are presented and agree well with the theoretical predictions. The results apply regardless of whether accelerations are produced by pressure waves in a non-steady flow or by curvature of streamlines in a steady flow. Various aspects of the experimental observations are discussed.

Type
Research Article
Copyright
© 1960 Cambridge University Press

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References

Birkhoff, G. & Caywood, T. E. 1949 Fluid flow patterns. J. Appl. Phys. 20, 646.
Bomelburg, H. J. 1956 A method for the measurement of the flow of air by means of series of electric sparks. Univ. of Marland, Tech. Note BN-68, AFOSR-TN-56-38.
Cady, W. M. 1954 In Physical Measurements in Gas Dynamics and Combustion, High Speed Aerodynamics and Jet Propulsion, pp. 13958, vol. IX. Princeton: Princeton University Press.
Herzog, J. 1957 A new experimental approach to the analysis of compressor performance. Univ. of Maryland, Tech. Note BN-90, AFOSR-TN-57-3.
Herzog, J. & Weske, J. R. 1957 Characteristics of the technique of aerodynamic investigation by means of electric sparks. Univ. of Maryland, Tech. Note BN-105, AFOSR-57-359.
Hirschfelder, J. O., Curtis, C. F. & Bird, R. B. 1954 Molecular Theory of Gases and Liquids. New York: Wiley.
Hoenig, S. A. 1957 Acceleration of dust particles by shock waves. J. Appl. Phys. 28, 1218.Google Scholar
Lamb, H. 1945 Hydrodynamics, 6th ed. New York: Dover.
Markstein, G. H. 1957 A shock tube study of flame front-pressure wave interaction. 6th Symposium (International) on Combustion, pp. 38798. New York: Reinhold.
Markstein, G. H. 1958 Discussion of Rudinger 1958.
Rudinger, G. 1958 Shock wave and flame interactions. Combustion and Propulsion, pp. 15382. Third AGARD Coll. London: Pergamon.
Saheki, Y. 1947 On the measurement of wind (tunnel) velocity (distributions) by the electric spark method. Hokkaido Univ., Faculty of Engineering Memoirs, 8, 185; transl. by E. Hope, Nat. Res. Counc. Can. Tech. Trans. TT-100 (1950).
Taylor, G. I. 1953 Formation of a vortex ring by giving an impulse to a circular disk and then dissolving it away. J. Appl. Phys. 24, 104.Google Scholar
Townend, H. C. H. 1937 Visual and photographic methods of studying boundary layer flow. Aero. Res. Counc. (Gt Brit.), Res. and Mem. no. 1803.
Turner, J. S. 1957 Buoyant vortex rings. Proc. Roy. Soc. A, 239, 61.Google Scholar
Weske, J. R. 1958 Ein Beitrag zur Untersuchung stetiger und unstetiger dreidimensionaler Strömungsfelder in Turbomaschinen. ZAM IXb (5/6) 721 (J. Ackeret Anniversary issue).
Wright, F. H. 1951 The particle-track method of tracing fluid streamlines. Jet Propulsion Lab., Calif. Inst. of Technology, Progress Rept, no. 3–23.