摘要
为了进一步提高低速大迎角试验数据的质量,掌握支架干扰规律,对Φ3.2m风洞张线尾撑系统进行了支架干扰试验研究。研究结果表明:张线尾撑装置的横梁对飞机纵向的远场干扰量较小,大迎角区域内尾支杆对飞机纵向的近场干扰量较大;迎角小于15°范围内,支架使飞机偏航力矩系数减小、滚转力矩系数增大,随侧滑角增大支架干扰量增大;去掉立尾后尾支杆对俯仰力矩的干扰明显减小。
In order to improve test data accuracy and acquire support interference characteristics, the test study on the support interference of wire-assistant sting support setting inФ3.2m low speed wind tunnel is introduced. It is shown that, the impact of the beam of wire-assistant sting support on longitudinal aerodynamics characteristics of aircraft is small, and the sting has great effect on longitudinal aerodynamics characteristics at high angle of attack. The yawing moment coefficients decrease and rolling moment coefficients increase at angle of attack from 0°to 15° with the existence of wire-assistant sting support. With the increase of side slip angle, the interference become bigger; without the vertical tail, the effect of the wire-assistant sting support on the pitching moment becomes small evidently.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2011年第3期1-5,共5页
Journal of Experiments in Fluid Mechanics
关键词
大迎角
张线尾撑
支架干扰
尾支杆
风洞实验
high angles of attack
wire-assistant sting support
support interference
sting
wind tunnel test
