在上海市应用数学和力学研究所SIAMM400 低速低湍流度风洞中, 对自行设计的GA-1060 机翼在低雷诺数下复杂三维绕流的气动性能进行了相关的实验研究, 并与NACA0012 翼型形成的矩形机翼绕流气动性能进行了比较. 结果表明: 在低雷诺数下GA-1060 机翼前缘较为钝厚, 有一定弯度, 厚度较小的外形使其具有更好的综合气动特性; 在较大攻角情况下, 升力系数和升阻比等参数均有较大提高, 6° 攻角时升阻比可增加到27%; 流动分离与翼尖涡的相互作用在一定程度上影响了翼尖涡的生成和发展.
Based on the wind tunnel of SIAMM400 provided by Shanghai Institute of Applied Mathematics and Mechanics, experiments were carried out on aerodynamic characteristics near GA-1060 wing under low Reynolds numbers. The results show that GA-1060 wing with blunt leading edges and bend trailing edges,and small thickness, has better aerodynamic performances in comparison with the original airfoil (NACA0012). Especially for those with large attack angles, the lift coefficient and lift-drag ratio are improved by 27% at α=6°. Moreover, formation and development of the wing tip vortex is influenced by the interaction with flow separation and wing tip vortex.
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