A series of experiments are performed to investigate the effect of steady loading and separated flow on the unsteady vortical gust response of both low and high solidity blade rows, including the effects of airfoil camber. 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. This provides the ability to quantify the steady or mean performance of the stator row over a range of steady loading levels both with and without unsteady flow effects. In particular, for a particular mean stator angle-of-attack, the steady and mean aerodynamic performance are determined in a steady flow and also in an unsteady flow generated by a rotor composed of perforated plates at the same mean operating condition. This enables the stator vane row dynamic stall conditions to be identified. The unsteady aerodynamic response of both symmetric and cambered stator vanes configured as low and high solidity stator vane rows is then investigated over a range of mean angle-of-attack values, including attached and separated flows with dynamic stall.

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