Abstract: The supersonic distributor for the inlet stage of a turbomachine comprises an outer case, a hub, and a set of peripheral blades disposed in a ring and attached to the hub to provide supersonic speed fluid passages between the blades to transform a flow at high pressure and low speed into a supersonic flow at low pressure. The blades are disposed radially in regular manner within a fluid feed torus. In a section developed on a line corresponding to a given radius, i.e. in a blade-to-blade plane, the blades define a profile in the form of a two-dimensional half-nozzle. This profile has a rectilinear upstream portion, a bulge defining a throat for accelerating the flow to a Mach number equal to 1, the throat being of section that varies with radius, and a downstream portion which terminates in a region of uniform flow at a trailing edge which may be truncated perpendicularly to the axis of rotation.