Abstract
This paper presents an experimental and numerical study of interaction of an oblique shock wave and a detached shock wave formed ahead of a circular cylinder.Measurements of pressure distribution and shock shape are made on circular cylinder at free stream Mach number of 2.48 and for 27.5° shock impingement. Next, supersonic flow over a circular cylinder is computed in the plane of symmetry of the flow field. A time-dependent second-order finite difference method is used to solve the equations for a perfect gas. The shock wave is treated as a discontinuity, across which the RANKINE-HUGONIOT relations are used to compute the flow conditions behind the shock.It is shown that an upward subsonic jet is formed right below the impingement point and therefore increases the shock detachment distance.
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