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以大型客机某方案机翼为基本翼,基于N-S方程数值模拟的方法,研究融合式翼梢小翼后缘操纵舵面偏转对机翼空气动力特性影响。研究发现,翼梢小翼舵面偏使得机翼气动特性发生显著变化。一方面,偏转舵面导致了机翼最大升阻比的降低,然而它可以优化不同飞行阶段升阻比。其中,舵面外偏,机翼在阻力增加不大的条件下,升力明显增大,有利于提高起飞、爬升性能;舵面不偏条件下升阻比最大,有利于提高巡航效率;舵面内偏,机翼阻力明显增大,有利于提高飞机着陆性能。另一方面,舵面偏转可以控制机翼翼梢涡的发展,有助于耗散机翼尾涡及激发翼梢涡自身的不稳定性而加速耗散。
Based on the numerical simulation of a N-S equation, a wing of a large passenger aircraft is taken as a basic wing. The aerodynamic characteristics of the wing are studied by the deflection of the tail edge of the integrated wingtip. It is found that the aerodynamic characteristics of the wing change significantly due to the deflection of the wingtip wing. On the one hand, deflecting the rudder surface leads to a reduction of the maximum lift / drag ratio of the wing, however, it can optimize the drag ratio at different flight stages. Among them, the rudder outer surface, the wing in the resistance increases little under the conditions of lift significantly increased, help to improve the take-off and climb performance; rudder unbalanced conditions down the largest resistance ratio is conducive to improving cruise efficiency; rudder surface Partial, wing resistance was significantly increased, help to improve aircraft landing performance. On the other hand, the rudder deflection can control the development of wing tip vortex, which can dissipate the wing vortex and dissipate the instability of wing tip vortex itself.