Effect of Hysteresis on Efficiency of Compressor Cascades During Streamlining by Unsteady Flows

Abstract

The effect of stalled flow hysteresis in the process of streamlining a cylindrical solid, isolated backswept wing of a model aircraft and a decelerating compressor cascade is analyzed in the given article. The structure and the performances of stalled flows depending on the speed of the flow, angles of attack and on the direction of their change are considered. Generalized results of research of hysteresis effect occurrence in aerodynamic performances of compressor cascades and its influence on compressor blade rings performances that operate in real conditions of periodic circular inlet distortion induced by aerodynamic trail behind the blade cascade of the compressor inlet guide vane are demonstrated.