摘要
选用Ｊ７飞机，在ｈ＝５０００ｍ，Ｍａ＝０．８，全加力飞行状态，使用倍脉冲平尾进行飞行试验所测得的两组试验数据及极曲线，对其Ｃｘ＝ｆ（Ｃｙ），Ｃｙ＝ｆ（α）中出现的不合理现象和疑点进行了分析和解释，并提出了解决办法。该解决问题的办法就是用动态飞行试验数据求出Ｃωｚｙ＝ｆ（Ｃｙ），（Ｍａ＝ｃ），并将此数据用于动态极曲线Ｃｙ平衡状态的修正。结果表明，用倍脉冲平尾求飞机极曲线的修正方法简便实用，是切实可行的。
This paper only choose two sets of polar curve measured in flight at h =5 000 m, Ma =0 8,full afterburner condition by J7 aircraft using double pulse horizontal tail,various contradictions and questions occured at C x=f(C y),C y=f(α) were analyzed and explained,and the solution was provided.That is giving C ωz y=f(C y)(Ma=c) by using dynamic flight test data, and using them in balance condition revision of C y for dynamic polar curve.The C y measured in flight is revised to C y in balance condition for positive ω z ,resulting induced drag factor value A is increasing rather than reducing.
出处
《飞行力学》
CSCD
北大核心
1998年第4期68-71,共4页
Flight Dynamics
