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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 further improve the quality of test data at high speed and low angle of attack and to grasp the law of stent interference, the stent interference experiment on the tailing system of Φ3.2m wind tunnel was carried out. The results show that: the cross beam of the tailing device has less interference with the aircraft in the far field in the longitudinal direction of the airplane, and the near-field interference with the tail boom in the high-angle of attack region is larger than the aircraft with the angle of attack less than 15 °. The aircraft yaw moment coefficient is reduced, the rolling torque coefficient is increased, and with the side slip angle is increased, the amount of interference of the supporter increases; the interference of the tail mast on the pitch moment is obviously reduced after the tail is removed.