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The starting process in a hypersonic nozzle

Published online by Cambridge University Press:  28 March 2006

C. Edward Smith
C. Edward Smith
Affiliation:
Department of Engineering Science, University of Oxford, England and Lockheed Missiles and Space Company, Palo Alto, California
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Abstract

This paper describes an experimental study of the starting process in a reflected-shock tunnel, and compares the results with numerical calculations reported previously (Smith 1962). It is shown that an unsteady expansion wave dominates the transient flow, and the shock-wave system plays a minor role. The effects of initial pressure in the nozzle were investigated, and the behaviour of the secondary shock wave was noted. It was found that initial pressures larger even than the steady-flow static pressure can be tolerated without prolonging the starting process, despite the presence of a strong secondary shock wave. Other analyses, based on the ‘steady-state’ model of the starting process, are discussed and shown to give an unrealistic description of the flow field.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 24 , Issue 4 , April 1966 , pp. 625 - 640
Copyright
© 1966 Cambridge University Press

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References

Ackroyd, J. A. D. 1964 Studies on the running time in a shock tube and shock tunnel. Ph.D. Thesis, University of London.
Alpher, R. A. & White, D. R. 1958 Flow in shock tubes with area change at the diaphragm section. J. Fluid Mech. 3, 457.Google Scholar
Bird, G. A. 1959 The effect of wall shape on the degree of reinforcement of a shock wave moving into a converging channel. J. Fluid Mech. 5, 60.Google Scholar
Chester, W. 1960 The propagation of shock waves along ducts of varying cross-section. Advances in Applied Mechanics, VI, p. 119. New York: Academic Press.
Chisnell, R. F. 1957 The motion of a shock wave in a channel, with applications to cylindrical and spherical shock waves. J. Fluid Mech. 2, 286.Google Scholar
Glass, I. I. & Hall, J. G. 1959 Handbook of Supersonic Aerodynamics, 18: Shock tubes. NAVORD Rep. no. 1488 (vol. 6).
Glick, H. S., Hertzberg, A. & Smith, W. E. 1955 Flow phenomena in starting a hypersonic shock tunnel. Cornell Aero Lab. Rep. no. AD-789-A-3.Google Scholar
Henshall, B. D. 1960 Experimental results from the NPL hypersonic shock tunnel Hypersonic Flow, Colston Papers. London: Butterworths.
Henshall, B. D. & Gadd, G. E. 1956 Factors affecting the performance of the nozzle of a hypersonic shock tube. ARC CP 293.Google Scholar
Hertzberg, A. 1956 The application of the shock tube to the study of the problems of hypersonic flight. Jet Propulsion, 26, 549.Google Scholar
Holder, D. W. & Schultz, D. L. 1962 The duration and properties of the flow in a hypersonic shock tunnel. Hypersonic Flow Research, Prog. in Astronautics and Rocketry (vol. 7). New York: Academic Press.
Lewis, C. H. & Burgess, E. G. 1964 Charts of normal shock wave properties in imperfect nitrogen. Arnold Engineering Development Center, Rep.no. AEDC-TDR-64–104.
Moore, F. K. 1951 Unsteady laminar boundary-layer flow. NACA TN 2471.Google Scholar
Parks, E. K. 1952 Supersonic flow in a shock tube of divergent cross-section. Univ. of Toronto, UTIA Rep. no. 18.Google Scholar
Smith, C. E. 1962 An analytic study of the starting process in a hypersonic nozzle. Ph.D. Thesis, Stanford Univ.
Smith, C. E. 1964 An analytic study of the starting process in a hypersonic nozzle. Proc. of Heat Transfer and Fluid Mech. Institute, p. 198. Stanford Univ. Press.Google Scholar
Stewartson, K. 1964 The Theory of Laminar Boundary Layers in Compressible Fluids. Oxford: Clarendon Press.
White, D. R. 1958 Influence of diaphragm opening time on shock-tube flows. J. Fluid Mech. 4, 585.Google Scholar
Wittliff, C. E., Wilson, M. R. & Hertzberg, A. 1959 The tailored-interface hypersonic shock tunnel. J. Aero. Sci. 26, 219.Google Scholar