Abstract
Running propellers can have a profound effect on the trim and static stability of an airplane. The method most commonly used for determining propeller stability derivatives is based on blade element theory with the axial component of induced velocity taken to be that predicted from classical propeller momentum theory, which neglects the effects of slipstream rotation. The induced flow that is predicted by classical propeller momentum theory is not consistent with the actual induced flow in the vicinity of a rotating propeller. In the present paper, an alternative method for predicting propeller stability derivatives is proposed. This method is based on blade element theory with the induced velocity predicted from propeller vortex theory. Nomenclature
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