J7L飞机大迎角/失速/尾旋试飞  

J7L high AOA/stall/spin flight test

作　　者：王启[1] 李树有[2] 张培田[2] 吴菊英[3] 

机构地区：[1]中国飞行试验研究院科技部,陕西西安710089 [2]中国飞行试验研究院飞机所,陕西西安710089 [3]空军工程大学电讯工程学院,陕西西安710077

出　　处：《飞行力学》2001年第4期58-61,66,共5页Flight Dynamics

摘　　要：介绍了 J7L飞机大迎角 /失速 /尾旋试飞的目的 ,简要说明了大迎角 /失速 /尾旋试飞前的预先研究工作 ,并结合具体的试飞结果曲线对 J7L飞机失速 /尾旋特性及改出方法进行了分析。结果表明 ,该方法可用于常规布局飞机的大迎角 /失速 /尾旋试飞 ,为新机试飞提供了有效的参考依据。The objectives of J7L high AOA/stall/spin flight are introduced. The procedure and results of analysis and prediction in advance before the flight test are described briefly. The stall/spin characteristics and recovery techniques of the J7L aircraft are analyzed and discussed based on the flight test results. The results show that these methods can be used to the high AOA/stall/spin flight test of normal design aircraft, and the effective reference support are provided for increasing the potential capability of the aircraft and the flight test of new types of aircraft.

关 键 词：大迎角 失速 尾旋 J7L飞机 试验飞行 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]