The effects of high steady loading and separated flow on the unsteady aerodynamic response of turbomachine blade rows are experimentally investigated. This is accomplished utilizing a unique single-stage turbomachine research facility in which the flow is not generated by the blading but rather by an additional fan. Thus, for a particular stator incidence angle, the steady or mean stator aerodynamic performance were determined in a completely steady flow with no rotor and also with unsteady flow generated by a rotor composed of perforated plates at the same mean operating condition, thereby identifying the stator vane row dynamic stall conditions. The unsteady aerodynamic response of the very low-solidity stator vane row is then investigated over a range of incidence angle values, including attached and separated flows with dynamic stall.

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