反弹自消散系统尾涡控制机制研究

为了研究加快尾涡消散的机理,以获得更合理的尾流间隔,进行了壁面反弹实验的数值模拟计算。实验采取在模拟机翼后缘安置反弹面的方法,诱发反弹二次涡与主涡相交出现不稳定性,以加快尾流衰减。数值计算运用N-S方程,对雷诺应力项采用Realizableκ-ε涡粘模型进行计算,分析经二次涡干涉后尾涡轴向涡量衰减、涡核下沉运动等参数的变化,以探究反弹二次涡对飞机主涡消散的演变影响。实验结果表明,反弹涡对主涡衰减有明显的促进作用。该实验为人工干预缩减机场尾流间隔的研究奠定了理论基础。

Research on the wake vortex control mechanism of the rebound self dissipation system

In order to reduce wake vortex separation, wake vortex dissipation technique was therefore introduced, the numerical simulation of wall bounce test was carried out.A rebound wall was established in the computational flow field via numerical simulation, which may lead to the intersection and fusion of the secondary-generated vortex and the primary wake vortex, so as to quicken the decay of vortex.Reynolds stress is computed based on Realizable κ-ε turbulence viscosity models.Moreover, locations of vortex core, vorticity dissipation, wake vortex horizontal separation and dimensionless parameters were compared for analysis.Moreover, research on the law of the rebound secondary vortex dissipation is of significance to accelerate the dissipation of the main vortex of the aircraft, as well as provides more reliable data and theoretical basis for manual reduction technologies of airport wake flow interval.