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Simple Formulae for Supersonic Flow past a Cone
Published online by Cambridge University Press: 07 June 2016
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.
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- Copyright © Royal Aeronautical Society. 1975
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