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.
A small perturbation of the second order of an incompressible laminar curved jet referred to the orthogonal curvilinear coordinate system is calculated. Using a parameter of small perturbation, which is expressed by a power of the arc length of the curved jet, non-similar velocity fields are calculated. Some properties of curved jets along a circular arc with a constant pressure difference across the stream are studied and it is found that the total rate of entrained flow is not changed for the jet with different curvatures.
The rarefied flow fields near a sharp leading edge of a flat plate immersed in a weakly ionized supersonic argon were analyzed theoretically. The BGK kinetic equations were solved numerically and the behaviours of the neutral and the charged particles in the region very near to the leading edge were obtained. Also, the detail structures of a shock wave and a boundary layer were made clear through the present analysis. The calculated density profiles for both neutral and charged species showed the shock formation processes in the leading edge region. The temperature of ions did not differ very much from that of neutral particles throughout the whole flow field. The calculated slip velocity and the shock wave shapes agreed reasonably well with the experimental results obtained from the low density arc heated wind tunnel.
The specific problem treated in this paper is the transient wave near the struck end propagating along the layers in an elastic laminated composite which is semi-infinite in length and is suddenly loaded by surface pressure applied over the end of the structure. To treat the wave motion in a laminated composite, fundamental equations based on the diffusing continuum theory are employed. As an analytical method for the problem, a wave front expansion technique is used which was proposed by ACHENBACH and REDDY to seek solution for transient wave propagation in a linearly viscoelastic rod. In the present paper, this technique is extended and applied to a laminated medium comprised of two different materials, and the numerical results by the method are compared with those by the conventional FOURIER-LAPLACE transform technique.