Hostname: page-component-7479d7b7d-k7p5g Total loading time: 0 Render date: 2024-07-11T22:23:58.626Z Has data issue: false hasContentIssue false
  • English
  • Français

On the laminar compressible boundary layer with stationary origin on a moving 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 growth of the laminar compressible boundary layer on a moving flat wall is considered analytically for the case of zero velocity in the free stream outside the boundary layer. The results of this analysis are compared with other published results for the cases in which the free stream has some finite velocity. In all the cases considered in the present paper, the boundary layer is taken to originate at some stationary point on the moving wall. This type of boundary-layer flow occurs behind moving shock waves and it is argued that the case of particular interest in the present paper, that of the stationary gas outside the boundary layer, provides bounding values of such parameters as displacement and momentum thicknesses for shock-induced laminar boundary-layer flows.

Type
Research Article
Information
Mathematical Proceedings of the Cambridge Philosophical Society , Volume 63 , Issue 3 , July 1967 , pp. 871 - 888
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)Bernstein, L.Notes on some experimental and theoretical results for the boundary layer development aft of a shock in a shock tube. Aero. Res. Council Current paper 625 (1961).Google Scholar
(2)Mirels, H. Laminar boundary layer behind shock advancing into stationary fluid. NACA TN 3401 (1955).Google Scholar
(3)Mirels, H. Boundary layer behind shock or thin expansion wave moving into stationary fluid. NACA TN 3712 (1956).Google Scholar
(4)Nigam, S. D.Advancement of fluid over an infinite plate. Bull. Calcutta Math. Soc. 43 (1951), 149.Google Scholar
(5)Young, A. D.Skin friction in the laminar boundary layer in compressible flow. Aero. Quart. 1 (1949), 137.CrossRefGoogle Scholar