双缝襟翼带滑流效应的分布式动力气动设计OA

With the development of the low-altitude economy industry,distributed propeller propulsion technology for small and medium-sized aircraft has become a hot research direction.This paper proposes a transport aircraft scheme based on distributed propeller propulsion;based on numerical simulation,the sliding mesh unsteady calculation method is used to analyze the distributed power aerodynamic design of this aircraft model under a double-slotted flap lift augmentation configuration.The results show that:compared with installation on a clean wing section,the pow-ered high-lift effect of the propeller is more significant on the double-slotted flap lift wing section;and the improvement of the powered high-lift effect requires control of the slipstream region on the propeller's downstream side:by increas-ing the vertical offset of the propeller relative to the local wing leading edge,the flap can be kept in the slipstream re-gion at high angles of attack,resulting in better lift augmentation,while increasing the forward extension has an insig-nificant effect;secondly,it is necessary to reduce the separation of the fixed wing leading edge on the propeller's up-stream side at high angles of attack,increased vertical offset of the propeller leads to more severe flow separation,while the effect of forward extension is similarly insignificant.Under the same thrust,a larger-diameter propeller can be used to reduce separation at high angles of attack.When propellers mounted ahead of a double-slotted flap are of identical size,positioned at the same relative leading-edge location,and operate under equal total thrust,using more propellers can enhance the powered high-lift effect.