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边条翼双垂尾布局是新一代战斗机的主要布局形式,这种气动布局可能引起双垂尾抖振,是飞机设计中的一个技术关键。边条翼布局双垂尾的抖振特性实验研究在西北工业大学低速风洞进行,测试迎角范围:0°～50°。实验还将垂尾位置前移了30mm(15.8%垂尾平均气动弦长)进行测量,并将垂尾前后2种位置的响应进行了对比分析。对2种模型都测量了垂尾的根部弯矩响应和翼尖加速度响应的时间历程,经数据处理得出弯矩和加速度脉动响应的均方根值及功率谱密度分布。实验结果表明:1抖振主要发生在一弯模态;2当迎角达到20°后,翼根弯矩响应和翼尖加速度响应都急剧增加,抖振起始迎角约为20°;3抖振响应在迎角27～40°之间最大;4垂尾前后位置对抖振起始迎角影响不大,但对抖振响应强度有明显影响;5边条涡破裂是诱发边条翼布局双垂尾抖振的主要原因。
The double-tail layout of the edge wing is the main layout of the new generation of fighter jets. Such aerodynamic layout may cause double-tail chattering and is a key technology in aircraft design. The experimental study of double-tail chattering characteristics of edge-winged wings is carried out at low speed wind tunnel of Northwestern Polytechnic University. The range of attack angle is 0 ° ~ 50 °. The experiment also measured the vertical tail position by 30mm (15.8% vertical tail average pneumatic chord length), and compared the responses of the two positions before and after the tail. For both models, the time histories of the root bending moments and the tip responses of vertical tail were measured. The root mean square (RMS) and power spectral density distributions of the bending moment and acceleration responses were obtained by data processing. The experimental results show that: 1, the chattering occurs mainly in a bending mode; 2 when the angle of attack reaches 20 °, the wing root bending moment response and the wing tip acceleration response increase sharply, and the starting angle of buffeting is about 20 °; 3 The chattering response is the largest between the angles of attack of 27-40 °. The position of 4 vertical tail has little effect on the initial attack angle of chattering, but has a significant effect on the chattering response strength. Layout of the main reason for double vertical tail buffeting.