不同尾旋动态下飞机尾流场数值仿真

Numerical simulation of aircraft tail flow field under different spin models

为分析不同尾旋动态下飞机尾流场分布情况及对方向舵效能的影响,运用计算流体力学技术,以国外某飞机为研究对象,对不同迎角下的尾旋飞机尾流场进行数值仿真计算,将仿真得到的方向舵效率变化情况和风洞试验数据进行对比,二者规律一致,表明计算模型构建合理。根据所建模型,从气流流动、压强、方向舵效率3个方面对不同尾旋动态下的飞机尾流场进行了分析,分析结果表明:大迎角下机翼和平尾上表面均存在严重气流分离,产生负压区;不同尾旋动态时方向舵效率始终存在,在改出尾旋过程中应反方向蹬舵。

In order to analyze the aircraft tail flow field under different spin models and the influence on the rudder efficiency,this paper takes a foreign aircraft as the research object,using computational fluid dynamics(CFD)technology to perform numerical simulation calculations on the aircraft tail flow field at different angles of attack(AOA).The numerical model was applied to calculate the rudder effectiveness at different angles of attack,and the results show a good agreement with the wind tunnel test data.According to the established model,the flow characteristic,the pressure as well as the rudder effectiveness under different spin models were analyzed.The results show that,negative pressure arises from flow separation at high angle of attack,the rudder will be an effective recovery control surface when it opposites to the direction of spin.