Plane contours with maximum thrust in a non-isentropic flow

Plane tasks of the contour and maximum thrust nozzle modelling in the supersonic flow with shock waves are formulated and solved analytically and numerically. The first of the considered problems relates to the optimal profiling of the tail part of the body. This part consists of some corner point, followed by straight section and following him, unknown in advance curved section on which the shock interaction of the flow with the wall occurs. To improve the characteristics of the "shock" contours the exact solution of the corresponding optimization problem in the class of straight segments is considered. The second problem relates to the construction of a plane supersonic nozzle of maximum thrust in the class of contours similar to those considered in the first problem. The isentropic flow is modeled by the flow from a supersonic source. This approach allows to find the initial shape of the optimal "impact nozzle" for the subsequent improvement of its shape using a numerical method of calculation. Parametric calculations of the flow in the supersonic part of the nozzle consisting of conical and parabolic sections and its thrust are carried out which is compared with the thrust of the equivalent conical nozzle.