For aircraft that employ distributed propeller propulsion systems, the distributed propeller slipstream increases the analysis complexity. The objective of this paper is to rapidly analyse the influence of propeller slipstream on a wing using a fast prediction approach to perform conceptual design studies. This fast approach is implemented through a panel/viscous vortex particle hybrid method taking into account the air viscosity effect. The parametric studies of propeller streamwise, spanwise, vertical installed position, propeller number and rotational direction are conducted for a rectangular wing platform in two different propeller-wing configurations. The results indicate that the propeller slipstream causes both the augmentations of the wing lift and drag in a traditional tractor propeller layout. For an over-the-wing propeller configuration, however, the obvious lift increase and drag decrease can be obtained. A rear propeller position relative to the wing chord leads to a beneficial increase in lift while a fore propeller location is able to decrease the wing drag. The maximum increment of the lift-to-drag ratio can be achieved by 17.6% when the propeller is located at 30% of the wing chord, which shows a considerable advantage in improving the wing aerodynamic efficiency.

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