摘要
为了研究前缘缝翼尾缘剪切层对多段翼气动性能的影响,通过在前缘缝翼尾缘添加喷流的方式来改变缝翼尾缘处的剪切层。选取不同的喷流流量和流速等参数,利用CFD手段研究了喷流对缝道的速度分布以及多段翼各个翼面气动力的影响。多段翼二维非定常流场由有限体积法求解的二维非定常雷诺平均Navier-Stokes方程得到。分析结果得到:前缘缝翼尾缘添加喷流后对多段翼各个翼面压力分布和最大升力系数均有较大影响,其中,主翼最大升力系数、总的最大升力系数、前缘缝翼和后缘襟翼升力系数随着喷流动量系数增加而增加。
Effect of jet applied to the leading edge slat on the flowfield for multi-element airfoils were investigated to improve the high-lift aerodynamic performance of multi-element airfoils. The influences of key parameters, such as the jet flow rate and the speed of jet on the leading edge slat were studied. CFD method was adopted to analyze the effect of jet on the aerodynamic performance and the shear layer development behind the gap between slat and main element. Two dimensional unsteady Reynolds-averaged Navier-Stokes equations was solved by finite volume method to obtain two dimensional unsteady flowfield of multi-element airfoils. The results indicated that the slat trailing edge jet flow has significant effect on the pressure coefficient of each section of the multi-element airfoils and the maximum lift coefficient simultaneously. The maximum lift coefficient, the total maximum lift coefficient of main element, and the lift coefficients of slat and flap would increase with the jet momentum coefficient increases.
出处
《空气动力学学报》
CSCD
北大核心
2017年第2期220-228,共9页
Acta Aerodynamica Sinica
关键词
前缘缝翼
多段翼
喷流
最大升力系数
缝道
slat
multi-element airfoils
jet
maximum lift coefficient
gap
