关键词: 动力增升, 双缝襟翼, 分布式推进, 螺旋桨, 滑移网格

Abstract:

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 powered 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 increasing the vertical offset of the propeller relative to the local wing leading edge， the flap can be kept in the slipstream region at high angles of attack， resulting in better lift augmentation， while increasing the forward extension has an insignificant effect； secondly， it is necessary to reduce the separation of the fixed wing leading edge on the propeller’s upstream 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.

Key words: powered high-lift, double-slotted flap, distributed propulsion, propeller, sliding mesh