Simple Formulae for Supersonic Flow past a Cone
- 1 February 1975
- journal article
- research article
- Published by Cambridge University Press (CUP) in Aeronautical Quarterly
- Vol. 26 (1) , 11-19
- https://doi.org/10.1017/s0001925900007150
Abstract
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.Keywords
This publication has 2 references indexed in Scilit:
- Inviscid Hypersonic Flow Over Unyawed Circular ConesJournal of the Aerospace Sciences, 1960
- The air pressure on a cone moving at high speeds.—IProceedings of the Royal Society of London. Series A, Containing Papers of a Mathematical and Physical Character, 1933