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 °, 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 , de-flection 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.%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.
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