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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
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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.

Information

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

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References

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