Investigation of annular supersonic inlets with isentropic compression

A technique for designing the supersonic annular inlets with isentropic deceleration surfaces is considered. The contour of an isentropic supersonic nozzle constructed by the method of characteristics for an inviscid gas flow with given uniform parameters at the inlet and at the outlet is used as the basic configuration of the inlet. The reversed flow of a viscous gas is computed with the aid of numerical techniques in the contour under consideration and the real operational characteristics of the obtained inlet of a fixed geometry are determined in the range of the conditions of its application. In the process of computations, the minimum cross-sectional sizes are selected, which ensure the inlet start without a detached bow shock at the entrance.