摘要
针对边条弯扭及改变双立尾展向位置对全机纵横向气动特性的影响进行了试验研究。结果表明 :边条弯扭可以在一定程度上提高最大升力系数 ,增加航向稳定的迎角范围 ,但对滚转稳定的迎角范围没有什么影响。当双立尾分别移到机身外侧置于机翼上时 ,可以显著提高全机最大升力系数 ,同时使航向和滚转稳定的迎角范围大为扩展。
An experimental study of the effects of the twin vertical fins position and twist strake wing on a fighter aerodynamic characteristics was performed in the wind tunnel. The result shows that the twist strake wing is able to increase the maximum lift coefficient and incidence range of yawing stability. However, it has no effect on rolling stability. When twin vertical fins are located at the wing surface the maximum lift coefficient could be increased obviously and the incidence range of yawing and rolling stability is extended.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2002年第2期170-172,共3页
Acta Aeronautica et Astronautica Sinica
