Abstract
An analysis is presented showing that the present practice of using a free flight/wind tunnel equivalence concept derived for steady flow will not correctly simulate the unsteady flow effects when estimating the impact of dynamic stall on the performance of axial flow compressors and helicopter rotors. Furthermore, not even a free flight/wind tunnel equivalence concept derived for unsteady inviscid flow will correctly simulate the dynamic stall characteristics because of the unsteady viscous boundary condition at the airfoil surface, the so-called moving wall effect. c / k Ka
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