A grid fusion lifting surface suitable for large subsonic angles of attack was designed. The influence of the grid position, grid diversion angle, and grid number on the aerodynamic performance of the grid fusion lifting surface under subsonic conditions was studied by numerical simulations. Based on the summary and analysis of the grid in the hypersonic state, the CFD numerical simulation method, which solves unsteady Reynolds averaged Navier-Stokes equations, was used to complete the research of the flow mechanism of the grid fin in the subsonic state. At low speed and subsonic conditions, the results show that the negative front grid fusion lift surface has better aerodynamic characteristics with a high angle of attack. Under subsonic conditions, the stall angle of attack of the front grid fusion lifting surface with a diversion angle of 20° increases by 16°, and the maximum lift coefficient increases by 22.1% compared to that of the conventional flat wing. The number of grids has an insignificant effect on the aerodynamic performance of the grid fusion lifting surface at a large angle of attack.

中文翻译：

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网格融合升力面及其大迎角流动控制机制

设计了一种适用于大亚音速攻角的网格融合升力面。通过数值模拟研究了亚音速条件下网格位置、网格导流角和网格数量对网格融合升力面气动性能的影响。在对网格在高超声速状态下的总结和分析的基础上，采用求解非定常雷诺平均Navier-Stokes方程的CFD数值模拟方法，完成了对网格翅片在亚音速状态下的流动机理的研究。结果表明，在低速亚音速条件下，负前栅融合升力面具有较好的气动特性，具有大迎角。在亚音速条件下，偏航角为20°的前格栅融合升力面失速攻角比常规平翼增加16°，最大升力系数增加22.1%。网格的数量对网格融合升力面在大迎角下的气动性能影响不大。