多段翼型前缘缝翼吹气流动与噪声控制数值研究  

Computational Investigation of the Slat Blowing and Noise Control for High-Lift Airfoil

作　　者：刘沛清[1] 崔燕香 屈秋林[1] 郭保东[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《民用飞机设计与研究》2012年第2期6-12,共7页Civil Aircraft Design & Research

摘　　要：根据吹气边界层流动控制的特点，探索了前缘缝翼流动控制和减噪技术。利用FLUENT软件对某多段翼型进行数值模拟，求解RANS方程和FW—H声学方程。在前缘缝翼下翼面设置吹气孔，通过改变吹气系数，研究缝翼缝道内吹气流动控制对二维多段翼型气动性能及噪声特性的影响。计算结果表明：应用缝翼吹气技术可在相同迎角下获得更高的升力系数，且能减小缝翼缝道内的分离，降低角涡引起的噪声；不同吹气系数对多段翼升力和噪声有不同程度的影响；迎角为6°时，吹气控制可以使低频噪声减少2～4．5dB。Based on the characteristics of blowing control, a new technique was put forward to weaken slat cove separation and reduce farfield noise. The effect of the slat blowing control on lift performance, the flow field and noise spectra with a three-element high-lift aerofoil was investigated by using the computational fluid dynamics （CFD） code of Fluent, the Reynolds-averaged Navier-Stokes equations and FW-H acoustic analogy. The blowing holes were set on the lower surface of the slat. By using the slat blowing technique, the slat cove separation can be controlled efficiently and the lift coefficient increased. The aerodynamic performance varies with different blowing coefficients. As compared to the baseline configuration, the noise content in low-frequency range in blowing control cases is reduced by 2 -4.5dB on the average.

关 键 词：吹气控制 缝翼噪声 减噪 流动分离 高升力翼型 

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]