Abstract
A low speed wind tunnel investigation was conducted to examine the effect of a pusher propeller on a 65 deg sweep delta wing. Two different propeller diameters were evaluated. The data showed that the pusher geometry can cause a delay in vortex breakdown yielding an increase in lift at high angles of attack. Surface pressure measurement showed that the propeller increased suction levels on both the leeward and windward surfaces, limiting lift enhancement. Lift augmentation was observed to favor low advance ratios.
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