Abstract
It is well known that the problem of the supersonic non-viscous and non-heat-conducting gas flow around an arbitrary blunt body is reduced to the solution of the boundary value problem for the system of equations of gas dynamics with three independent variables. If a streamlined body has a sufficiently long shape the complete problem is logically divided into two problems. The first problem is to determine the flow in the head part between the separated shock and the body in the region G 1 where equations are of the mixed type. The second problem is to determine a flow in the purely supersonic region G 2 (Fig. 1a) where equations are hyperbolic.
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