Mathematical modeling of shock wave interaction at supersonic flight of a group of bodies

The results of numerical studies of spatial supersonic flows in a disturbed region of two similar jointly streamlined bodies placed in parallel at the freestream Mach number $M_\infty = 4.03$ and the zero angle of attack are presented. Two similar configurations placed in parallel are represented as the combinations of a cone with the semivertex angle equal to $20^\circ$ and a cylinder with an elongation of 5. The second-order finite-difference scheme used is based on the approximation of Euler' equations in integral form. The problem is solved along a march coordinate in the longitudinal direction, using the global iterations. It is shown that the shorter distance between the bodies, the greater effect of diffracted shock waves on loads distributed over the configuration surface and on their overall aerodynamic characteristics. The numerical results are compared with experimental data.