采用机头边条改善飞机大迎角横侧气动特性的风洞试验研究

Wind Tunnel Investigation of Nose Strakes for Improvement of Lateral and Directional Aerodynamic Characteristics at High Angle of Attack

飞机大迎角横侧气动特性是决定其机动性及敏捷性的主要因素之一。本文就采用机头边条改善飞机大迎角横侧气动特性进行了讨论。着重对机头边条的大小、安装位置等对飞机稳定性的影响进行讨论。试验是在气动中心低速所４ｍ×３ｍ和３．２ｍ风洞中进行的。

It was investigated to improve aircrafts directional aerodynamic characteristics at high angle of attack by using nose strakes in 4m×3m and 3.2m wind tunnel.The result was shown to be highly effective in improving F x 1 aircrafts directional stability,the shape of strake and its mounted location(longitudinal or circumferential).It was also highly effective in yaw control effectiveness in a wide range of angles of attack,especially in 40°≤α≤60°.