非涡核区域尾涡遭遇快速建模方法

基于Hallock-Burnham尾流速度模型,建立了尾涡流场、滚转力矩及最大坡度计算模型。通过对非涡核区域尾涡遭遇的仿真,计算尾涡流场中不同位置的飞机最大坡度,按坡度大小进行尾涡流场区域危险等级划分,确定流场中不同危险等级的分布范围;研究分析了飞机飞行高度、重量、马赫数以及前后机间隔等因素的变化对飞机尾涡遭遇的具体影响。通过案例分析计算,验证了模型的快速性,可用于尾涡流场非涡核区域危险性分析。

Research on rapid modeling method for wake vortex encounter in non-vortex core region

Based on the Hallock-Burnham wake velocity model, the calculation model of wake vortex flow, rolling moment and maximum slope angle is established. By simulating the wake vortex encounter in the non-vortex core region, the maximum bank angle of the aircraft at different positions in the wake vortex flow field is calculated. According to the bank angle, the hazard level of the wake vortex flow field is divided to determine the distribution range of different hazard levels in the flow field. The specific effects of changes in aircraft flight altitude, aircraft weight, aircraft Mach number and flight separation were analyzed on the wake vortex encounter. Through the case analysis and calculation, the rapidity of the model is verified, which can be used for the risk analysis of the non-vortex core region of the wake vortex flow field.