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对民用客机上使用较多的两种翼尖装置(融合式翼梢小翼和翼尖涡扩散器)进行了对比分析与研究。在基本机翼参数相同的基础上,利用ICEM软件对基本机翼及分别加装两种不同翼尖装置的机翼生成点对点对接的高质量多块结构化计算网格,采用Roe三阶迎风偏置通量差分裂方法和隐式近似因子分解法求解耦合SA湍流模型的雷诺平均Navier-Stokes方程。通过计算得知:在巡航状态下分别加装融合式小翼和翼尖涡扩散器后,两种机翼的升阻比分别提高了10.945%和4.993%,俯仰力矩系数分别增加了9.410%和5.116%,翼根弯矩系数分别增加了7.380%和1.013%。分析结果表明:相比于翼尖涡扩散器,融合式翼梢小翼能更显著地提高机翼的升阻比,但同时也较为明显地增加了机翼的俯仰力矩和翼根弯矩,从而导致飞机配平阻力和翼根结构重量的增加。
Two types of wingtips (fusion wingtip and wingtip vortex diffuser), which are widely used on civil passenger aircraft, are compared and analyzed. Based on the same basic wing parameters, ICEM software was used to generate high-quality multi-block structured computational grids with point-to-point connection to both the basic wing and the wing with two different wingtips respectively. Roe’s third- Reynolds Average Navier-Stokes Equations for Solving Coupled SA Turbulence Models with Inverse Flux Splitting and Implicit Approximation Factorization. The calculation results show that the lift-drag ratios of the two airfoils increase by 10.945% and 4.993%, respectively, and the pitching moment coefficients increase by 9.410% and 5.116%, and the root bending moment increased by 7.380% and 1.013% respectively. The analysis results show that, compared with the tip-vortex diffuser, the fusion wingtip can significantly improve the lift-drag ratio of the wing, but also obviously increases the wing pitch moment and wing root bending moment, Resulting in increased airplane trim resistance and wing-root structure weight.