应 用 协 同 射 流 原 理 的 旋 翼 翼 型 增 升 减 阻 试 验 研 究

As the novel active flow control technology，Co-flow Jet concept（CFJ）is one of the most potential methods to achieve the high lift enhancement and drag reduction of rotor airfoil. Based on the OA312 rotor airfoil，the CFJ rotor airfoil dynamometric model driven by the micro ducted fan group is designed. The low-speed wind tunnel test of high lift enhancement and drag reduction of rotor airfoil using Co-flow Jet concept with zero mass and high negative pressure at the leading edge is conducted. The influence of basic parameters such as the injection size，suction size and suction surface translation on lift enhancement and drag reduction is studied. The optimal values of key parameters of CFJ rotor airfoil are given. Results show that compared with the OA312 baseline airfoil，the CFJ rotor airfoil can significantly reduce drag coefficients at low angle of attack，and even achieve“negative drag”while the zero-lift pitch moment is basically unchanged. The CFJ rotor airfoil can significantly increase the maximum lift coefficient and the stall angle of attack at high angle of attack. The maximum lift coefficient can be increased by about 67.5%，and the stall angle of attack is significantly delayed by nearly 14.8°.