扰流板下偏对增升装置气动性能的影响及流动机理研究  

Study on Flow Mechanism and Aerodynamic Characteristic of High-Lift Devices with Drooped Spoiler

作　　者：刘江[1] 郑隆乾[2] 白俊强[1] 沈广琛[1] 刘睿[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]上海飞机设计研究院,上海200232

出　　处：《西北工业大学学报》2017年第5期813-820,共8页Journal of Northwestern Polytechnical University

基　　金：国家"973"计划(2014CB744804)资助

摘　　要：采用计算流体力学方法,针对有、无扰流板下偏的二维和三维增升装置进行数值模拟,研究了扰流板下偏对着陆构型气动性能的影响及其流动机理。结果表明:相比于初始构型,扰流板下偏且保持缝道参数不变时,可以改善着陆构型的气动性能,线性段在相同迎角下的升力系数明显增大,最大升力系数也增大;当扰流板下偏角度增大到10°时,线性段升力系数上移0.2左右,最大升力系数增大了约4.2%。流动机理分析表明:一方面,扰流板下偏可以增大主翼的弯度和环量,造成对缝翼的上洗作用以及襟翼的下洗作用增强,结果使主翼和缝翼的升力增大,襟翼的升力减小,最终体现在总的升力增大;另一方面,扰流板下偏,有利于增强缝道射流的柯恩达效应,改善襟翼上表面附面层的速度型,延缓了分离区的出现,对襟翼升力的减小具有一定的抑制作用。Taking advantage of computational fluid dynamics, the simulation of two-dimensional and three-dimen- sional high-lift devices with deflection of spoiler or not was done. The flow mechanism and aerodynamic characteristic of high-lift devices landing configuration with drooped spoiler were studied. The result indicated that the aerodynamic performance of the landing configuration can be improved when the spoiler deflected and the pa- rameters of the gap and overlap were kept constant compared with the initial configuration, the lift coefficient of the linear section at the same angle of attack significantly increased, and the maximum lift coefficient also increased; When the spoiler deflection angle increased to 10 o, the linear section of the lift coefficient moved up about 0.2 and the maximum lift coefficient increased by about 4.2%. The analysis of the flow mechanism showed that ： on the one hand, the camber and circulation of the main wing can be enhanced by the deflection of spoiler, and the washing effect on the slat and the flushing effect on the flap were enhanced, as a result , the lift of main wing and slat in- creased and the lift of flap decreased , which was reflected in the increase of the total lift; on the other hand, deflection of spoiler is helpful to enhance the Coanda effect of the slotted jet and improve the speed of the upper sur- face of the flap, resulting in delaying the emergence of the separation zone and restraining the decrease of the flap lift.

关 键 词：扰流板下偏 CFD 增升装置 流动机理 气动性能 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]