低速飞机加装翼梢小翼的CFD数值计算及风洞试验研究

详细信息

The computational and experimental investigation on winglets of a low speed aircraft

摘要: 针对某四发涡桨飞机飞行速度较低,巡航升力系数较大的特点,通过加装翼梢小翼改善翼尖流场特性而提高巡航升阻比。经数值计算和风洞试验验证表明,几何参数优化后的小翼,可以使飞机久航点升阻比提高8%,远航点升阻比提高4.8%。加装翼梢小翼气动特性的CFD数值计算和风洞试验结果吻合良好,可作为小翼外形进一步优化后快捷、经济的验证手段。
- 翼梢小翼 /
- 升阻比 /
- 诱导阻力 /
- CFD数值计算 /
- 风洞试验
Abstract: An aircraft with four turbo-propeller engines is characterized by low speed and relative high cruise lift coefficient.Winglets are utilized to improve the flow condition around the wing tips and increase the lift-to-drag ratio.CFD calculation and wind tunnel tests show that the lift-to-drag ratio at endurance cruise can be increased by 8%,while the lift-to-drag ratio at range cruise can be increased by 4.8% after the optimization of geometric parameters.The results of CFD simulation about the aerodynamic characteristics of the winglet agree well with wind tunnel test results, which could be a convenient and economic method for further optimization of winglet geometry.