后缘连续偏转机翼振荡射流控制的数值模拟研究  

Numerical Simulation of Oscillating Jet Control for Trailing Edge Continuous Deflection Wing

作　　者：刘影 李春鹏[1] 张铁军[1] 钱战森[1] Liu Ying;Li Chunpeng;Zhang Tiejun;Qian Zhansen(Aero Science Key Lab of High Reynolds Aerodynamic Force at High Speed,AVIC Aerodynamics Research Institute,Shenyang 110134,China)

机构地区：[1]中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《航空科学技术》2020年第5期36-43,共8页Aeronautical Science & Technology

基　　金：国家研究项目“变弯度机翼技术(VCAN)”。

摘　　要：针对民用飞机连续偏转后缘机翼在起降大偏度状态由于后缘流动分离导致升力损失的问题,选取振荡射流发生器开展流动控制机理和应用研究。首先基于二维流场通过给定不同入口参数分析了控制器内外流场结构的变化规律,然后选取典型民机机翼二维翼段,通过对常规开缝后缘襟翼和有/无控制器的连续偏转后缘开展升力特性和流场结构的对比,分析了振荡射流发生器在三维流场的流动控制能力。结果表明,振荡射流发生器能够通过输出周期性摆动的高速射流有效消除后缘翼面分离,使连续偏转后缘的升力达到与开缝襟翼相当的水平。In order to solve the problem of obvious flow separation leading to lift loss on the trailing edge of continuous deflection wing of civil aircraft under take-off and landing conditions,an oscillating jet generator is selected to study the flow control mechanism and application.Firstly,based on the two-dimensional flow field,the change rules of the flow field structure inside and outside the controller are analyzed by giving different inlet pressures.And then,a typical civil aircraft wing 2D wing section is selected.The conventional slotted trailing edge flaps and the continuous deflection of the trailing edge with and without the controller are used to compare the lift characteristics and the flow field structure,and the flow control ability of the oscillating jet generator in the three-dimensional flow field is analyzed.The results show that the oscillating jet generator can effectively eliminate the trailing edge airfoil separation by outputting a high-speed jet that periodically swings,so that the lift of the continuously deflected trailing edge reaches a level equivalent to that of the slotted flap.

关 键 词：振荡射流发生器 后缘分离 流动控制 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]