Abstract
A possibility of two-dimensional supersonic portion having quasi-axisymmetric flows which satisfy simplified radial equilibrium is investigated in this report. With the intension of getting a supersonic portion for practical use, the main requirements are given as follows. (1) The inlet flow is uniform and parallel to the axis. (2) The flow just before the normal shock is quasi-axisymmetric and satisfies simplified radial equilibrium. (3) The starting condition for a supersonic diffuser is satisfied between the inlet flow and the flow just before the normal shock. (4) The turning angle and the magnitude of deceleration in the supersonic portion are specified for the purpose of adequate blade thickness. The calculated examples are obtained at hub, mean and tip radii.
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