Subsonic Flow Region on Blunted Cones in Supersonic Flow

Abstract

This article investigates both experimentally and numerically the complicated flow around the blunted cone of semi-apex angle 20-45 degrees at Mach number 1.4-3.0. Especially, emphasized is the structure of subsonic flow region on the cone surface, that is caused by the transition from the over-expanded flow at the nose to the re-compression on the cone. Both results are in good agreement with each other. Consequently, it is shown that the numerical analysis of inviscid flow is very practical for such a complicated flow.