JL8飞机失速尾旋飞行试验研究  

Research on JL8 aircraft stall and spin flight test

作　　者：李雪琴[1] 宫西卿[1] 贾晓鹏[1] 吕玉虎[1] 

机构地区：[1]中国飞行试验研究院飞机所,陕西西安710089

出　　处：《飞行力学》2001年第2期57-61,共5页Flight Dynamics

摘　　要：叙述了 JL8飞机失速尾旋试飞状态、试飞方法和试飞结果。试飞结果表明 ,JL8飞机具有良好的大迎角特性及低速和高速失速特性。其正飞尾旋获得了三种模态 ,即“落叶飘”型非定常尾旋、非定常陡振荡尾旋和左均匀平尾旋 ;倒飞尾旋呈不稳定型态。而且各种尾旋都能成功地改出。另外 ,还评价了误操纵对失速和尾旋的影响。可供飞机大迎角和失速、尾旋特性研究人员参考。A Research of JL8 aircraft stall and spin flight test is described in this paper. The results of flight test show that JL8 aircraft has very good characteristics of high angle of attack, low speed and high speed stalls. Three modes are obtained in spin test. They are unsteady “drift leaf” spin, unsteady steep oscillatory spin and left steady flat spin. Inverted spin is unsteady. All spin are recovered successfully. The effects of incorrect control on stall and spin are evaluated. This paper is a very importand reference for high angle of attack, stall and spin flight test investigation.

关 键 词：失速 尾旋 飞行试验 JL8飞机 试飞方法 大迎角特性 不稳定型态 尾旋模态 

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] V217