基于数值模拟的飞机近场尾涡特征参数计算

Investigation of characteristic parameters of aircraft near-field wake vortex based on numerical simulation

尾流间隔是飞机起降和飞行过程的安全保障。近场尾涡特征参数是尾涡远场演变和消散研究的基础,是缩减尾流间隔以提升机场及空域容量的理论依据。采用雷诺平均法数值模拟A320飞机尾涡的近场演化过程,对近场尾涡特征参数的计算方法进行了研究。结果表明:与Hallock-Burnham模型相比,Lamb-Oseen模型能更准确地描述近场尾涡速度分布;采用平均椭圆法计算的近场尾涡涡核半径比采用传统方法计算的精度更高;数值模拟中,A320机型更适合采用3~12 m的平均环量值来描述近场尾涡强度。

Near-field wakes are key factors affecting the safety of aircraft landing and take-off.Accurate characterize these near-field wake vortices is the foundation for further studying the evolution of far-field wake vortices and also the theoretical basis for increasing the airspace capacity by reducing wake separations.The evolution of near-field wake vortices of an A320 aircraft is simulated by solving the Reynolds-Averaged Navier-Stokes equations.Computation methods for the characteristic parameters of near-field wake vortices are compared.Results show that compared to the Hallock-Burnham model,the Lamb-Oseen model can give a more accurate description of the velocity field induced by near-field wake vortices.The average ellipse method is more accurate than the traditional one in calculating the radii of the near-field wake vortices.Results also suggest that it is more proper to use an average circulation between 3 m to 12 m to describe the strength of near-field wake vortices of A320.