民用飞机尾旋特性预测与尾旋风洞试验验证  

Spin Characteristic Prediction and Verification for Civil Aircraft

作　　者：颜巍[1] 黄灵恩 YAN Wei;HUANG Lingen(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1期75-81,共7页Civil Aircraft Design & Research

摘　　要：通过查阅资料,收集在不同试验技术条件下研究所获得的不同固定翼飞机的尾旋特性数据,进行分析和比较获得了一些有意义的经验性结论。选取了几架在布局上与飞机A最为相似的飞机进行了尾旋特性的初步预测,并进一步利用飞机在完全发展尾旋条件下的力矩平衡原理,结合作图法(交点法)预测了飞机A在完全发展稳定尾旋条件下的攻角(α)与无因次旋转角速度(λ)。最后利用一个动力相似缩比飞机模型在尾旋风洞中进行尾旋试验研究,所获得的试验结果也印证了上述预测方法的合理性。Firstly,data collection of different spin characteristics of fixed wing aircrafts under the different test technology and conditions was carried out widely,and several important empirical conclusion were taken through analysis and comparison. The initial spin characteristic of aircraft A was predicted based on the spin characteristics of some other aircrafts which have got the similar layout. Further,according to the theory of moment equilibrium when aircraft is at the state of fully developed spin,the angle of attack and non-dimensional rotation speed of aircraft were predicted by using intersection method. Finally,the prediction was confirmed by the results of spin tunnel experiments,and a dynamic similarly scaled aircraft model was used. The test results confirm the rationality of the prediction method.

关 键 词：发展尾旋特性 交点法 尾旋风洞试验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]