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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。
In order to study the influence of the tailing shear layer of the leading edge on the aerodynamic performance of the multi-section wing, the shear layer at the trailing edge of the slat is changed by adding a jet to the trailing edge of the slat. Different parameters such as jet flow rate and velocity are selected to study the influence of jet velocity on the velocity distribution of the slot and the aerodynamic force of each wing of multi-segment wing by CFD. The two-dimensional unsteady flow field of a multi-stage wing is obtained from the two-dimensional unsteady Reynolds-averaged Navier-Stokes equations solved by the finite volume method. The analysis results show that the pressure distribution and the maximum lift coefficient of each airfoil have a great influence on the jet flow of the leading edge of the tail flap. Among them, the maximum lift coefficient of the main wing, the total maximum lift coefficient, The lift coefficient of trailing edge flaps increases with the increase of jet momentum coefficient.