低速大迎角张线尾撑系统支架干扰影响研究  

Study on the support interference of wire-assistant sting support at high angle of attack in low speed wind tunnel

作　　者：祝明红[1] 孙海生[1] 金玲[2] 汤伟[2] 刘志涛[2] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2011年第3期1-5,共5页Journal of Experiments in Fluid Mechanics

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.

关 键 词：大迎角 张线尾撑 支架干扰 尾支杆 风洞实验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V211.74