Rotating Stall in Axial Flow Compressors

The classical theories of linearized aerodynamics yields a complete description of the flow field due to the rotating stall in a two-dimensional cascade of airfoils, when the extension of the stalled region is small. The corresponding physical scheme can be used for larger stalled regions, without the limitations of the linearizing assumptions, if no through flow is assumed through the stall zones. Experimental researches on a single rotor confirm the results of the theoretical calculations, where the mean radius section of the rotor is described by means of a two-dimensional model.