摘要
尾流间隔缩减方法的最终目标是根据机场上空风场以及前后机配对,实时计算两机尾流间隔。由于进近阶段背景风场环境复杂,为达成这一阶段目标,有必要针对不同背景风场,对前机的尾流场进行研究。论文选择气流颠簸这一近地面常见风结构进行CFD数值模拟研究,观察NACA4415二维翼型在遭遇气流颠簸时的流场结构并对其现象进行了解释。模拟结果说明飞机在遭气流颠簸时二维机翼受垂直方向周期性波动的流场会加快尾流涡量场的断裂。在机翼后方会产生随周期上下波动的湍流,湍流强度在向后发展过程中横穿流线会导致湍流强度的降低。在经过机翼后,机翼后缘附近流线方向主要受机翼前缘与来流夹角影响,约两倍弦长后受背景风场影响扬起或落下,周期与来流周期一致。
The ultimate goal of the wake interval reduction method is to calculate the wake interval between the two aircraft in real time based on the wind field over the airport and the pairing of the front and rear aircraft.Due to the complex environment of the background wind field during the approach phase,in order to achieve the goal of this phase,it is necessary to study the wake field of the front aircraft for different background wind fields.In this paper,turbulence,a common wind structure near the ground,is se-lected for CFD numerical simulation,and the flow field structure of NACA4415 two-dimensional airfoil when encountering turbu-lence is observed and explained.The simulation results show that when the plane is tossed by the air current,the two-dimensional wing of the two-dimensional wing will be accelerated by the rupture of the wake vortex field due to the vertical fluctuation of the flow field.Turbulence that fluctuates up and down with the cycle will be generated behind the wing,and the turbulence intensity will de-crease when the turbulence intensity crosses the streamline during the backward development process.After passing the wing,the direction of the streamline near the trailing edge of the wing is mainly affected by the angle between the leading edge of the wing and the incoming flow.After about twice the chord length,it will rise or fall under the influence of the background wind field,and the period is consistent with the incoming flow period.
作者
王靖开
潘卫军
韩帅
许亚星
WANG Jingkai;PAN Weijun;HAN Shuai;XU Yaxing(School of Air Traffic Management,Civil Aviation Flight University of China,Guanghan 618307)
出处
《计算机与数字工程》
2024年第5期1546-1551,共6页
Computer & Digital Engineering
基金
国家自然科学基金项目“近地阶段飞机尾流演化与风险控制关键技术”(编号:U1733203)
民航局安全能力建设项目“基于飞机尾流预测的缩减管制间隔技术研究”(编号:TM2018-9-1/3)
民航专业项目(编号:TM2019-16-1/3)
四川省科技计划项目(编号:2021YFS0319)
中央引导地方科技发展项目(编号:2020ZYD094)资助。
关键词
CFD
数值模拟
翼尖涡
气流颠簸
尾流间隔缩减
CFD
numerical simulation
wingtip vortex
turbulence
reduce wake interval
作者简介
王靖开,男,硕士,研究方向:数值模拟、空中流量管理;潘卫军,男,博士,教授,研究方向:空中交通管理、计算机仿真;韩帅,男,硕士,研究方向:数值模拟、飞行程序设计;许亚星,男,硕士,研究方向:冲突告警、碰撞风险。
