Hostname: page-component-77c89778f8-vpsfw Total loading time: 0 Render date: 2024-07-17T06:29:30.017Z Has data issue: false hasContentIssue false
  • English
  • Français

A Note on the Thin-Shock-Layer Approximation

Published online by Cambridge University Press:  07 June 2016

R Hillier  and
B A Woods
R Hillier
Affiliation:
Imperial College
B A Woods
Affiliation:
University of Canterbury, New Zealand
Get access

Summary

This Note proposes a restriction on possible solution procedures for thin-shock-layer theory. This restriction has been widely violated in solutions presented hitherto, although with negligible error apparently. Those cases are indicated where failure to apply the restriction leads to definite errors.

Type
Research Article
Information
Aeronautical Quarterly , Volume 28 , Issue 2 , May 1977 , pp. 85 - 89
Copyright
Copyright © Royal Aeronautical Society. 1977

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

1 Messiter, A F Lift of slender delta wings according to Newtonian theory. AIAA Journal, Vol 1, p 794, 1963.CrossRefGoogle Scholar
2 Squire, L C Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds. Aeronautical Quarterly, Vol XIII, p 185, 1967.Google Scholar
3 Squire, L C Some extensions of thin-shock-layer theory. Aeronautical Quarterly, Vol XXV, p 1, 1974.Google Scholar
4 Hillier, R The effects of yaw on conical wings at high supersonic speeds. Aeronautical Quarterly, Vol XXI, p 199, 1970.Google Scholar
5 Shanbhag, V V Numerical studies on hypersonic delta wings with detached shock waves. ARC Current Paper 1277.Google Scholar
6 Hayes, W D Probstein, R F Hypersonic Flow Theory. Vol 1, Academic Press, New York, 1966.Google Scholar