高速化是未来直升机的发展趋势之一。针对共轴高速直升机旋翼大反流区特点，开展了反流区翼型设计研究。首先分析了旋翼根部双钝头翼型在高速飞行状态下的绕流特点及减阻机理，然后针对旋翼反流区的工作环境，提出了一种“吸力面气动前缘半径大、中后部平坦”的双钝头翼型设计思路。相比于标准椭圆翼型，该翼型改善了顺/反流状态流动分离问题，在维持顺流状态低阻特性的同时，0.1Ma反流状态减阻可达10%以上。以该翼型为基准，开展考虑吸力面流动特征的混合反设计/优化设计。优化翼型维持了反流状态的低阻特性，且顺流状态升阻特性显著提升
Higher speed is development tendency of helicopter in the future. Considering the wide region reverse flow of coaxial high-speed helicopter, carried out a study of reverse flow airfoil design. Firstly, analysed the flow characteristic surrounding blunt trailing edge airfoil and drag reduction mechanism deployed in root of rotor at the state of high speed forward flight, and subsequently designed a blunt trailing edge airfoil characterized by “large radius in leading edge and smooth in middle and rear at suction surface”, in consid-eration of the reverse flow environment of rotor. Compared with standard elliptic airfoil, the modified airfoil improves the flow sepa-ration both in reverse flow and forward flow, and drag coefficient decreases more than 10% at 0.1 Ma in reverse flow, meanwhile maintains low drag characteristics at 0.3Ma and 0.5Ma in forward flow. Based on the modified airfoil, carried out airfoil hybrid in-verse design and design optimization considering flow characteristic in suction surface. Result indicates that the optimized airfoil maintains low drag coefficient in reverse flow, and the lift-drag characteristic is promoted in forward flow observably.
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