发动机内部流量对飞机尾旋特性的影响研究  

Effect of Engine Internal Flux on Aircraft Spin Characteristics

作　　者：颜巍[1] 黄灵恩 周敏[1] YAN Wei;HUANG Ling＇en;ZHOU Min(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《民用飞机设计与研究》2018年第3期36-40,共5页Civil Aircraft Design & Research

摘　　要：为了研究某型民用飞机的高涵道比发动机不同内部流量对飞机尾旋特性的影响,首次通过在飞机自由尾旋模型的发房内部添加能模拟不同通气流量的堵块,在尾旋风洞中进行自由尾旋试验和改出试验。通过试验发现,添加模拟不同发房通气流量堵块对模型尾旋中的攻角和偏航角速率没有明显的影响,对尾旋改出特性也没有本质的影响;但对模型在尾旋中的滚转角速率和侧滑角有影响,随着通气量的减小和阻塞效应的增大,滚转角速率和侧滑角随时间记录数据的振幅也在增加。而左右发房通气量的不对称对飞机模型的尾旋特性有明显的影响。To investigate the different engine internal flux effect on spin characteristics for some civil aircraft with high bypass engine,several light weight block which can control the engine internal flux was mounted inside of nacelle of an aircraft free-spin model. Based on the spin tunnel test results, these blocks have got less effect on angle of attack,yawing speed and recovery characteristics,but these blocks have got significant effect on rolling speed and sideslip angle, when engine internal flux decreases, blockage effect is increased, the oscillation of recorded data of rolling speed and sideslip angle is dramatically increased. Moreover, asymmetry of left and right engine internal flux has got obviously effect on aircraft model spin characteristics.

关 键 词：民用飞机 发房内部流量 尾旋特性 尾旋改出 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]