Abstract
A calculation is presented of the flow around axially-symmetric and close to axially-symmetric bodies with a circular throat and a tapering central body by a supersonic stream of an ideal gas at an angle of attack and regimes with a detached shock wave. The method of solution is based on a treatment of the flow in the coupled meridional half-planes of the cylindrical coordinate system in each of which the problem is solved using the Godunov finite-difference scheme and an approximation of the dependence of the flow functions on the meridional angle by means of trigonometric polynomials. An algorithm is proposed for isolating the three-dimensional shock wave, the surface of which has a particular cleavage line (the line of points of the ternary interaction of the shock waves). The possibilities of the method are demonstrated by means of examples.
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