Hostname: page-component-848d4c4894-tn8tq Total loading time: 0 Render date: 2024-06-28T18:02:18.549Z Has data issue: false hasContentIssue false

On the stable shape of subliming bodies in a high-enthalpy gas stream

Published online by Cambridge University Press:  28 March 2006

Peter G. Simpkins
Affiliation:
Department of Aeronautics, Imperial College of Science and Technology

Abstract

This paper describes a series of experiments carried out in a high-enthalpy stream of argon on materials that are known to sublime. The results confirm that an axisymmetric Teflon model ablates to a stable shape which is independent of the initial nose profile. The effect of changing the total enthalpy of the gas is simply to alter the recession rate of the nose. The experimental results show poor agreement with a simple theory which ignores the effects of mass transfer in the boundary layer.

Type
Research Article
Copyright
© 1963 Cambridge University Press

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Amdur, I. & Mason, E. A. 1958 Properties of gases at very high temperatures. Phys. Fluids, 1, 370.Google Scholar
Bade, W. L. 1962 Stagnation point heat transfer in a high temperature iner gas. Phys. Fluids, 5, 150.Google Scholar
Bogdonoff, S. M. 1957 Exploratory studies of hypersonic fluid mechanics. AGARD Rep. no. 142.Google Scholar
Buckingham, R. A. 1957 Numerical Methods, p. 298. London: Pitman.
Christensen, D. & Buhler, R. D. 1958 On the stable shape of a slender ablating graphite body. J. Aero. Sp. Sci. 26, 54.Google Scholar
Christensen, D. & Buhler, R. D. 1959 Arc jet measurements related to ablation test validity. Symposium on reinforced Plastics for Rockets and Aircraft. Amer. Soc. for Testing Materials.
Chu, S. T. & Lee, J. D. 1959 Steady state fusible body shapes in a heated supersonic and hypersonic stream. 6th Mid-Western Conference on Fluid Mechanics, p. 71.
Georgiev, S., Hidalgo, H. & Adams, M. C. 1959 On ablation for the recovery of satellites. AVCO Res. Rep. no. 47.Google Scholar
Harvey, J. K. & Simpkins, P. G. 1961 A description of the Imperial College archeated wind tunnel. Imperial College Rep. no. 110, also J. Roy. Aero. Soc. 66, 637.Google Scholar
Lees, L. 1956 Laminar heat transfer over blunt nosed bodies at hypersonic flight speeds. Jet Prop. 26, 259.Google Scholar
Lees, L. 1959 Ablation in hypersonic flows. 7th Anglo-American Conf., New York.
Low, G. M. 1955 The compressible laminar boundary layer with fluid injection. NACA TN no. 3404.Google Scholar
McLellan, C. H. 1955 Trans. ASME, 77, 727.
Roberts, L. 1959 Mass transfer cooling near the stagnation point. NASA TR R-8.Google Scholar
Settlage, P. H. & Siegle, J. C. 1961 Behaviour of ‘Teflon’ fluorocarbon resins at elevated temperatures. Planetary & Space Sci. 3, 73.Google Scholar
Stetson, K. F. 1960 Boundary layer transition on blunt bodies with highly cooled boundary layers. J. Aero. Sp. Sci. 27, 81.Google Scholar
Stine, H. A. & Windlass, K. 1954 NACA TN, no. 3344.
Sutton, G. W. 1959 On the stable shape of a slender ablating graphite body. J. Aero. Sp. Sci. 27, 681.Google Scholar
Tate, A. 1959 An equilibrium profile for the melting of long axisymmetric bodies due to kinetic heating. 9th Tripartite AXP Res. Conf., Canada, ARC 21, 726.
Wood, C. J. 1962 Hypersonic flow over spiked cones. J. Fluid Mech. 12, 614.Google Scholar
Wright, M. S. 1956 High Temperature Technology, p. 106 (ed. I. E. Campbell). New York: J. Wiley.