Investigation of Propeller-Wing Interaction Based on the Sliding Mesh Technology

The aerodynamic characteristics of propeller-wing interaction for the Rocket Launched UAV were simulated numerically based on the High Performance Computing Cluster System by means of sliding mesh technology. The results showed that the effects on the wing made by the rotating propeller were much notable. The forces and moments data were collected for axial wing placements ranging from 0.056 to 0.5D and varied rotating speeds. A representative portion of a data set for the speed setting of 6000rpm and fixed Z_o=0 was included show the various forces and moments. The drag can be seen to remain relatively constant as the aircraft moved progressively closer to the propeller until the wing was positioned at 0.056D downstream of the propeller, where a nearly 20% increase occurred. Based on the pressure cloud and streamlines, the vortices generated by propeller, propeller-wing interaction, and wing-tip were captured and analyzed.