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钝头体窄条翼布局导弹在大攻角下拥有极为优异的纵向气动特性,但横向容易失稳,做快速机动时容易诱发非指令的横向不稳定运动。通过开展高速风洞自由摇滚试验和数值模拟,研究了窄条翼导弹自由摇滚特性和流动机理,试验与计算吻合较好。研究发现:较大迎角时,窄条翼面积中心距离尾舵前缘根部5~6倍直径时,模型会进入极限环摇滚,窄条翼位置对模型稳定性有显著的影响,去掉窄条翼或尾舵时,模型均不会进入摇滚;模型空间流场特性表明,气流经过窄条翼时形成的片涡,对背风舵产生强烈的干扰,抑制了尾舵涡的形成和发展,使背风舵动态失稳,导致模型进入极限环摇滚。
The blunt body narrow wing layout missile has extremely excellent longitudinal aerodynamic characteristics at high angles of attack, but is prone to instability in the lateral direction. It is easy to induce non-commanded transverse instability during fast maneuvers. The free rock test and numerical simulation of high-speed wind tunnel are carried out to study the free-rock characteristics and flow mechanism of narrow-wing missile. The experimental results are in good agreement with the calculated results. The results show that the model will enter the limit ring when the center of the narrow wing area is 5 ~ 6 times the diameter of the leading edge of the tail rudder at larger angle of attack. The position of the narrow wing has a significant effect on the stability of the model, Wing or tail rudder, the model will not enter the rock. The flow field characteristics in the model space show that the vortex formed when the air flow passes through the narrow strip wing has a strong interference to the rudder and restrains the formation and development of the rudder vortex Levitation dynamic instability, leading to the model into the limit ring rock.