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对飞机近场尾涡参数进行定量分析是研究尾涡运动、消散规律的基础,也是合理缩减空中交通尾流间隔的重要理论依据。采用有限体积法求解质量加权平均Navier-Stokes方程,湍流模型采用RSM模型,数值模拟了B757-200飞机的近场尾涡特性,并对飞机尾涡参数进行了相关计算。结果表明:在飞机尾涡的近场区域初始尾涡位置与飞机迎角无关;涡核间距随流向距离的增加线性减小;尾涡切向速度的最大值随流向距离的增加呈指数规律递减;涡核半径约为机翼展长的5%~10%。
The quantitative analysis of the wake vortex parameters in the near field of aircraft is the basis for studying the law of wake vortex movement and dissipating, and also an important theoretical basis for reasonably reducing the wake interval of air traffic. The finite volume method was used to solve the mass weighted average Navier-Stokes equations. The turbulence model was simulated by RSM model. The near-field wake vortex characteristics of the B757-200 were numerically simulated and the wake vortex parameters were calculated. The results show that the initial wake position is not related to the angle of attack of the aircraft in the near-field region of the tail vortex. The vortex core spacing decreases linearly with the increase of the flow distance. The maximum value of the tangential velocity decreases exponentially as the distance increases ; Vortex core radius of about 5% to 10% of the wingspan.