新概念机翼尾流特性实验  

Experiment on a new concept wing layout with alleviated wake vortex

作　　者：朱睿[1] 刘锦生[2] 刘志荣[1] 鲍锋[1] 

机构地区：[1]厦门大学航空航天学院,厦门361005 [2]清华大学航天航空学院,北京100084

出　　处：《航空学报》2017年第4期1-9,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11072206);福建省科学基金(2012J01023)~~

摘　　要：大型飞机常采用开启襟翼以增大机翼升力系数,实现较大迎角的起飞和降落,而机翼在大迎角状态下,翼尖会产生能量集中且自由消散时间长的飞机尾涡,严重影响后续起降飞机的安全。基于Rayleigh-Ludwieg不稳定性,提出一种新概念飞机襟翼布局,通过水槽实验发现:新概念布局的襟翼对翼尖涡的消散具有明显的促进作用,不同参数组合下襟翼涡对翼尖涡的运动特性和能量变化的影响均有不同。实验结果也为飞机尾流控制的研究提供了参考,在满足飞行力学设计的基础上,合理运用增升装置构建四涡系统可以有效促进飞机尾流的消散,提高机场飞机起降效率。Aircraft wake vortex will be produced by the wing tip to have a negative impact on flight safety,when a large aircraft applies flap wing to take-off and landing under a large angle of attack.Based on the Rayleigh-Ludwieg instability,a new concept flap layout is developed by adding a set of specially designed flaps.Water channel experiments reveal that the new concept flap layout can significantly promote the wingtip vortex dissipation.The wingtip vortex which is affected by flap vortex with disparate parameter combinations performs differently with respect to movement characteristics and energy.The experiments also provide references to wake vortex control,when the requirement for flight mechanics design is satisfied.Building four-vortex system reasonably by taking advantage of high-lift devices will has a significant effect on alleviating the intensity of aircraft wake,and improve the efficiency of aircraft take-off and landing at the airport.

关 键 词：飞机尾涡 Rayleigh-Ludwieg不稳定性 襟翼 粒子图像测速 水槽 

分 类 号：V211.76[航空宇航科学与技术—航空宇航推进理论与工程]