Abstract
Quasisteady supersonic flow over a flat cone on a plane surface is studied. A formula is derived for the angle through which the flow lines turn at the cone. The results are used to justify the use of two-dimensional simulations of the flow. Peak pressures and total impulses are obtained numerically for various cone angles.
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This article was processed using Springer-Verlag TEX Shock Waves macro package 1990.
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Book, D.L., Eidelman, S., Lottati, I. et al. Numerical and analytical study of transverse supersonic flow over a flat cone. Shock Waves 1, 197–203 (1991). https://doi.org/10.1007/BF01413794
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DOI: https://doi.org/10.1007/BF01413794