尾流冲浪中后机等效诱导升力计算分析
Calculation and analysis of equivalent induced lift in wake surfing
陈宽明 1王腾 1刘泽宇 2蒋倩兰 1邓蕾蕾1
作者信息
- 1. 中国民用航空飞行学院 空中交通管理学院,四川 广汉 618307
- 2. 太原国际机场有限责任公司,太原 030000
- 折叠
摘要
为进一步得到在尾流冲浪中的减阻、节油等效益,提出了一种尾流冲浪中后机获取升力的计算方法,对节油率进行分析.采取数值模拟的方法,选取A330-200 机型作为前机和后机,以其适用巡航速度在高空飞行作为背景,模拟了其尾涡的环量、半径以及其产生的下沉运动.根据尾流的耗散规律从2 000～4 500 m范围中选取了6 组前后机纵向间隔,参照不同的后机距涡核的相对位置进行了滚转力矩分析,根据诱导速度等效转化为后机均匀获取的诱导升力,分析评估出合理的后机冲浪位置,得出较高的节油率为12.28%.
Abstract
In order to further obtain the benefits of drag reduction and fuel saving in wake surfing,this paper proposes a calculation method for obtaining lift from the rear engine in wake surfing to analyze the fuel saving rate.This article adopts a numerical simulation method,selects the A330-200 model as the front and rear aircraft,and uses its applicable cruise speed as the background for high-altitude flight,simulates the circulation,radius,and sinking motion of its wake vortex.Based on the dissipation law of the wake,6 sets of longitudinal intervals between the front and rear engines were selected from the range of 2 000 meters to 4 500 meters.Rolling torque analysis was conducted with reference to the relative positions of the rear engine to the vortex core.The induced speed was equivalently converted into the induced lift uniformly obtained by the rear engine.Finally,a reasonable rear engine surfing position was analyzed and evaluated,and a high fuel saving rate of 12.28%was obtained.
关键词
尾流冲浪/数值模拟/尾涡/诱导速度/诱导升力Key words
wake surfing/numerical simulation/tail vortex/induced speed/induced lift引用本文复制引用
基金项目
国家自然科学基金(U1733203)
中国民用航空飞行学院面上项目(J2021-083)
中国民用航空飞行学院大学生创新创业训练计划(S202310624240)
出版年
2024
NETL
NSTL
万方数据