Potential Vortex Cascades for Supersonic Speeds

Summary

The concept of parallel flow at the inlet and at the exit of cascades, on which, for instance, the honored’s paper referenced under [1] is based, can be realized exactly in non-viscous supersonic flow. First, the transition from parallel supersonic flow with distinct Mach numbers into potential vortex flow is defined. With three sections, a transition section, a potential flow vortex section and another transition section which reinstates parallel exit flow, “Potential Flow Vortex Cascades” of arbitrary inlet and exit Mach numbers and of arbitrary flow deflection can then be constructed. This, together with some practical requirements, is illustrated by an example.

Translated by R. M. Markytan from K. Oswatitsch, “Potentialwirbel-Gitter für Überschallgeschwindigkeiten“, Zeitschrift für Flugwissenschaften (ZFW) 4 (1956), 53–57.