The leading edge of a body with a channel, flying at supersonic speed

A numerical study is made of the supersonic flow around the wedge-shaped leading edges of an antisymmetric body with a channel, in the case of a toroidal separated shock wave. The solution is obtained by the method of integral relations in a one-strip scheme in special variables taking into account the nature of the flow at the top of the edge. The effect of geometrical parameters of the body and of the Mach number of the incident flow is studied.