Hostname: page-component-78c5997874-94fs2 Total loading time: 0 Render date: 2024-11-20T02:45:37.698Z Has data issue: false hasContentIssue false
  • English
  • Français

On the laminar compressible boundary layer induced by the passage of a plane shock wave over a flat wall

Published online by Cambridge University Press:  24 October 2008

J. A. D. Ackroyd
J. A. D. Ackroyd
Affiliation:
Department of Aeronautical Engineering, Queen Mary College, University of London
Get access Rights & Permissions [Opens in a new window]

Summary

The laminar compressible boundary layer induced by the passage of a plane shock wave over a flat wall is examined in detail. Use is made of the empirical viscosity-temperature relationship μ ∝ Tω. The boundary-layer equations are solved numerically for various values of the index ω, Prandtl number and shock strengths. The resulting solutions are then used to construct simple semi-empirical relationships for some of the more important boundary-layer parameters.

Type
Research Article
Information
Mathematical Proceedings of the Cambridge Philosophical Society , Volume 63 , Issue 3 , July 1967 , pp. 889 - 907
Copyright
Copyright © Cambridge Philosophical Society 1967

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

REFERENCES

(1)Ackroyd, J. A. D. On the laminar compressible boundary layer with stationary origin on a moving flat wall. To be published.Google Scholar
(2)Crocco, L.Lo strato limite laminare nei gas. Monografie Scientifiche di Aeronautica 3 (available as R.A.E. Translation 218 (1947)).Google Scholar
(3)Hartunian, R. A. and Marrone, P. V.Viscosity of dissociated gases from shock-tube heat-transfer measurements. Phys. Fluids 4 (1961), 535.CrossRefGoogle Scholar
(4)Lagerstrom, P. A. Chapter 4 of Theory of laminar flows, p. 227 (Oxford University Press, 1964).Google Scholar
(5)Mirels, H.Boundary layer behind shock or thin expansion wave moving into stationary fluid. NACA TN 3712 (1956).Google Scholar
(6)Mirels, H.Laminar boundary layer behind a strong shock moving into air. NASA TN-D 291 (1961).Google Scholar
(7)Moeckel, W. E. and Weston, K. C.Composition and thermodynamic properties of air in chemical equilibrium. NACA TN 4265 (1958).Google Scholar
(8) Van Driest, E. R.Investigation of laminar boundary layer in compressible fluids using the Crocco method. NACA TN 2597 (1952).Google Scholar
(9)Young, A. D.Skin friction in the laminar boundary layer in compressible flow. Aero. Quart. 1, 137 (1949).CrossRefGoogle Scholar
(10)Young, A. D. Chapter 10 of Modern developments in fluid dynamics, high speed flow 1, 375 (Oxford University Press, 1953).Google Scholar