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The flow of a jet from a body opposing a supersonic free stream

Published online by Cambridge University Press:  28 March 2006

P. J. Finley
P. J. Finley
Affiliation:
Engineering Department, Cambridge University Present address: Engineering Department, University of Malaya, Kuala Lumpur.
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Abstract

A series of experiments is described in which a jet issues from an orifice at the nose of a body in supersonic flow to oppose the mainstream. An analytical model of the flow is developed which suggests that the aerodynamic features of a steady flow depend primarily on a jet flow-force coefficient, and the Mach number of the jet in its exit plane. A sufficient condition for steady flow is developed. The experiments are found to agree well with predictions based on the flow model. A short account is presented of some previous investigations, and some of their conclusions are re-examined in the light of the present study.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 26 , Issue 2 , October 1966 , pp. 337 - 368
Copyright
© 1966 Cambridge University Press

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References

Adamson, T. C. & Nicholls, J. A. 1959 On the structure of jets from highly under expanded nozzles into still air. J. Aero. Sci. 26, 16.Google Scholar
Baron, J. R. & Alzner, E. 1963 An experimental investigation of a two layer inviscid shock cap due to blunt body nose injection. J. Fluid Mech. 15, 442.Google Scholar
Benjamin, T. B. 1962 Theory of the vortex breakdown phenomenon. J. Fluid Mech. 14, 593.Google Scholar
Chapman, D. R., Kuehn, D. M. & Larson, K. H. 1957 Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition. NACA Rep. no. 1356.Google Scholar
Charczenko, N. & Hennessy, K. W. 1961 Investigation of a retro rocket exhausting from the nose of a blunt body into a supersonic free stream. NASA TN, no. D-751.Google Scholar
Cooke, J. C. 1963 Separated supersonic flow. RAE TN Aero 2879, ARC 24 935 (unpublished).Google Scholar
Ferri, A. & Bloom, A. 1957 Cooling by jets directed upstream in hypersonic flow. WADC TN, no. 56–382, ASTIA AD 97232.Google Scholar
Finley, P. J. 1963 Experiments on jets directed from blunt bodies against a supersonic airstream. Ph.D. Thesis, Cambridge University.
Hartmann, J. & Lazarus, F. 1941 The airjet with a velocity exceeding that of sound. Phil. Mag. (7), 31, 35.Google Scholar
Lopatoff, M. 1951 Wingflow study of pressure drag reduction at transonic speed by projecting a jet of air from the nose of a prolate spheroid of fineness ratio 6. NACA RM, no. L51E09.Google Scholar
Love, E. S. 1952 The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow. NACA RM, no. L52119a.Google Scholar
Love, E. S. 1957 A re-examination of the use of simple concepts for predicting the shape and location of detached shock waves. NACA TN, no. 4170.Google Scholar
Love, E. S., Grigsby, C. E., Lee, L. P. & Woodling, M. J. 1959 Experimental and theoretical studies of axisymmetric free jets. NASA TR, no. R-6.Google Scholar
Macmahon, H. M. 1958 An experimental study of the effect of mass injection at the stagnation point of a blunt body. GALCIT Hypersonic Res. Project Memo. no. 42.Google Scholar
Owen, P. R. & Thornhill, C. K. 1952 The flow in an axially symmetric supersonic jet from a nearly sonic orifice into a vacuum. ARC Rep. & Memo. no. 2616.Google Scholar
Pack, D. C. 1948 On the formation of shock waves in supersonic gas jets (two dimensional flow). Quart. J. Mech. Appl. Math. 1, 1.Google Scholar
Romeo, D. J. & Sterret, J. R. 1963 Exploratory investigation of the effect of a forward-facing jet on the bow shock of a blunt body in a Mach number 6 free stream. NASA TN, D-1605.Google Scholar
Stalder, J. R. & Inouye, M. 1956 A method of reducing heat transfer to blunt bodies by air injection. NACA RM, no. A56B27a.Google Scholar
Sutton, E. P. & Finley, P. J. 1964 The flow of a jet from the nose of an axisymmetric body in a supersonic airstream. Archiwum Mechaniki Stosowanej 3, 781.Google Scholar
Warren, C. H. E. 1960 An experimental investigation of the effect of ejecting a coolant gas at the nose of a bluff body. J. Fluid Mech. 8, 400.Google Scholar
Watts, G. A. 1956 An experimental investigation of a sonic jet directed upstream against a uniform supersonic flow. UTIA TN, no. 7.Google Scholar
Van Dyke, M. & Gordon, H. D. 1959 Supersonic flow past a family of blunt axisymmetric bodies. NASA TR, no. R-1.Google Scholar