Hostname: page-component-586b7cd67f-t7czq Total loading time: 0 Render date: 2024-11-26T02:34:15.273Z Has data issue: false hasContentIssue false
  • English
  • Français

Laminar Boundary Layers Behind Strong Moving Shock Waves

Published online by Cambridge University Press:  04 July 2016

J. A. D. Ackroyd
J. A. D. Ackroyd*
Affiliation:
Department of the Mechanics of Fluids, University of Manchester*
Get access Rights & Permissions [Opens in a new window]

Extract

The problem considered in the present note is that of the laminar boundary layer created by the motion of a strong shock wave. Such shock-induced boundary layers occur in shock tube flows behind the primary moving shock wave. For structural reasons, shock tubes frequently do not have very large diameters, so that such boundary layers often adversely affect the quality and duration of the test gas flow. The latter problem is studied, for example, in ref. 1 and to attempt such a problem a fairly detailed knowledge of the behaviour of shock-induced boundary layers is required. Such basic boundary-layer studies have been described in refs. 3-8 and the situation which occurs when the shock wave is strong is investigated here. The boundary-layer equations are expanded in a series form which involves a small parameter. This small parameter is shown to be the ratio of the gas densities fore and aft of a strong shock wave.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 74 , Issue 710 , February 1970 , pp. 155 - 159
Copyright
Copyright © Royal Aeronautical Society 1970 

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.)

Footnotes

*

At present on leave of absence at the Dept of Mechanical Engineering, US Naval Postgraduate School, Monterey, California.

References

1. Ackroyd, J. A. D. Some Further Notes on the Laminar Boundary Layer Development and Running Time in a Shock Tube. ARC CP 966, 1967.Google Scholar
2. Hayes, W. D. and Probstein, R. F. Hypersonic Flow Theory, Academic Press, 1959.Google Scholar
3. Mirels, H. Laminar Boundary Layer Behind a Strong Shock Moving into Air. NASA TN D-291, 1961.Google Scholar
4. Ackroyd, J. A. D. Wall Shear Stress and Heat Transfer for Shock-Induced Laminar Boundary Layers. AIAA Jnl, Vol 6, No 8, pp 1620–1621, August 1968.Google Scholar
5. Ackroyd, J. A. D. On the Laminar Compressible Boundary Layer Induced by the Passage of a Plane Shock Wave Over a Flat Wall. Proc Cam Phil Soc, Vol 63, Pt 3, pp 889–908, July 1967.Google Scholar
6. Mirels, H. Boundary Layer Behind Shock or Thin Expansion Wave Moving into Stationary Fluid. NACA TN-3712, 1956.Google Scholar
7. Ackroyd, J. A. D. On the Laminar Compressible Boundary Layer With Stationary Origin on a Moving Flat Wall. Proc Cam Phil Soc, Vol 63, Pt 3, pp 871–888, July 1967.Google Scholar
8. Hartunian, R. A. and Marrone, P. V. Viscosity of Dissociated Gases From Shock-Tube Heat-Transfer Measurements. Physics of Fluids, Vol 4, No 5, pp 535–543, May 1961.Google Scholar