为研究扭曲尾翼对飞行器气动特性的影响，引入扭曲率与平均攻角来表示尾翼的几何特征，通过求解旋转坐标系下的定常状态N-S方程，对十字型布局扭曲尾翼飞行器气动特性进行了数值仿真。结果表明：扭曲尾翼可以增加飞行器的滚转力矩和平衡转速，其平衡转速与扭曲率呈正比关系；随着扭曲率的增大，扭曲尾翼飞行器未转动时的阻力系数增大、平衡转速时阻力系数减小；在临界扭曲率以内，随着扭曲率的增加，飞行器平衡转速时翼面压力分布得到了有效改善，研究结果对于飞行器的气动构型设计及其飞行稳定性分析具有参考价值。%In order to study the influence of aerodynamic characteristics on the twist fin vehicle,twist rate and average attack angle was introduced to represent geometric features of tail.By solving the N-S equations in standing state in rotating frame,a numerical simulation of the aerodynamic characteristics of cruciform layout twist fin vehicle was made .The results show that the twist fin can increase the rolling moment and balancing speed of aircraft and the balancing speed is proportional to the twist rate.When the twist rate increases,the twist fin’s initial resistance coefficient increases.When the balancing speed is reached,the resistance coefficient will decrease.In the critical twist rate,increased with the twist rate,the wing surface pressure distribution will be improved effectively at the balancing speed.The research results have reference value for the aerodynamic configuration design stability design of vehicle.
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