摘要
为了研究某常规布局大型民用飞机的偏离特性与尾旋敏感性,在CARDC的FL-14水平风洞(Φ3.2m)中进行了飞机模型的大迎角静态测力试验。通过对试验结果的充分挖掘,利用一系列的稳定性判据进行分析,获得了飞机的大致初始偏离迎角和偏离区间,并预测了飞机的尾旋敏感性。
In order to study departure characteristics and spin sensitivity analysis for a large general layout civil aircraft,an aircraft model force and moment measurement tests were carried out in CARDC FL-14（ Φ3. 2m） horizontal wind tunnel. Base on the analysis of the experimental results and several stability criterion be used,a roughly initial departure angle of attack and departure region were obtained and spin sensitivity of aircraft was predicted.
出处
《民用飞机设计与研究》
2016年第2期32-36,共5页
Civil Aircraft Design & Research
关键词
大迎角试验
偏离特性
尾旋敏感性
high angle of attack experiments
departure characteristics
spin sensitivity
