Hostname: page-component-77c89778f8-m8s7h Total loading time: 0 Render date: 2024-07-19T00:49:02.493Z Has data issue: false hasContentIssue false
  • English
  • Français

Simple Formulae for Supersonic Flow past a Cone

Published online by Cambridge University Press:  07 June 2016

W H Hui
W H Hui*
Affiliation:
University of Waterloo, Ontario, Canada
Get access

Summary

The problem of the supersonic flow with attached shock wave past a circular cone at zero angles of attack is treated, using the thin-shock-layer expansion. The solution is calculated to the fourth approximation. A simple formula is then derived for the surface pressure coefficient by the application of the parameter-straining technique and it is shown to be very accurate for the whole Mach number range for which the shock remains attached to the cone vertex.

Type
Research Article
Information
Aeronautical Quarterly , Volume 26 , Issue 1 , February 1975 , pp. 11 - 19
Copyright
Copyright © Royal Aeronautical Society. 1975

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 Taylor, G I Maccoll, J W The air pressure on a cone moving at high speeds. Proc Roy Soc A, Vol 139, p 278, 1933.Google Scholar
2 Kopal, Z Tables of supersonic flow around cones. Technical Report No.1, Department of Electrical Engineering, Massachusetts Institute of Technology, 1947.Google Scholar
3 Sims, J L Tables for supersonic flow around right circular cones at zero angles of attack. NASA SP-3004, 1964.Google Scholar
4 Babenko, K I Voskresenskii, G P Lyubimov, A N Rusanov, V V Three-dimensional Flow of Ideal Gases around Smooth Bodies. Translated from the Russian, printed in Jerusalem by Monson, S, 1968.Google Scholar
5 Pottsepp, L Inviscid hypersonic flow over unyawed circular cones. Journal of the Aero/Space Sciences, Vol 27, p 558, 1960.Google Scholar
6 Hayes, W D Probstein, R F Hypersonic Flow Theory. Vol 1, Chapter 4, Academic Press, 1966.Google Scholar
7 Pritulo, M F The flow past a yawed delta wing. Fluid Dynamics Transactions, Vol 4, p 261, 1969.Google Scholar
8 Hui, W H On two-dimensional and axisymmetric flow with attached shock waves. Astronautica Acta, Vol 18, p 35, 1973.Google Scholar