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以麦道航空公司的三段增升构型为研究模型,采用剪切应力输运(SST)k-ω湍流模型在C-H型多块结构网格上求解二维非定常雷诺平均Navier-Stokes方程,研究了前缘缝翼微型后缘装置(MTED)在多段翼型被动流动控制中的应用。由于MTED改变了实际的缝翼缝道参数,因此首先研究了作为主要改变量的缝道宽度对该三段翼型气动性能的影响,当缝道宽度从参考构型的2.95%c增加至3.98%c时,最大总升力系数约减小4.61%。当在不同缝道宽度基本构型上增加相同MTED时,计算结果表明它对各个翼段的影响定性一致,即前缘缝翼升力增加、主翼升力减小以及后缘襟翼升力基本不变化。这些升力变化的综合作用是:MTED构型线性段总升力系数的变化不大,失速段的变化取决于缝道宽度,当缝道宽度为3.98%c时,高度为0.50%c的MTED构型的最大总升力系数约增加6.98%。
Taking McDonnell Douglas-Williams’ three-stage ascending model as the research model, two-dimensional unsteady Reynolds average Navier-Stokes equations are solved on multi-grid CH grids using the shear stress transport (SST) k-ω turbulence model The application of the front slat mini trailing edge device (MTED) in the passive flow control of multi-section airfoil. As the MTED changed the actual slat seam parameters, the influence of the slot width as the main change on the aerodynamic performance of the three-section airfoil was studied. As the width of the slot increased from 2.95% c of the reference configuration to 3.98 % c, the maximum total lift coefficient decreased by about 4.61%. When the same MTED is added to the basic configuration of width of different slits, the calculation results show that it has the same qualitative effect on each wing segment. That is, the lift of the leading slat increases, the lift of the main wing decreases and the lift of the trailing edge flap does not change basically. The combined effect of these lift changes is that the total lift coefficient of the linear section with MTED configuration does not change much, and the change of the stall section depends on the width of the slot. When the slot width is 3.98% c, the MTED configuration with a height of 0.50% c The maximum total lift coefficient increased by about 6.98%.