摘要
为了更好地改善飞机的气动性能,以柔性变形机翼为研究对象,在仿真软件上采用不可压缩流体的雷诺平均方程与k-ω SST湍流模型进行了气动特性研究。通过对柔性偏转机翼与传统偏转机翼以及柔性偏转机翼自身之间的比较,对比并分析了9种不同变形情况的机翼气动特性。结果表明:对比传统偏转机翼,柔性变弯度机翼的升阻力系数以及升阻比在迎角-10°~7°处有所不同;并通过对多种柔性变形机翼的参数进行分析,得出转轴位置、变形范围、偏转角度3个参数对气动特性的影响规律:即为了得到更优的升阻特性,随着迎角不断增加,应选择处在弦长百分比较小的转轴位置、较小的偏转角度以及更大的变形范围。
In order to better improve the aerodynamic performance of the aircraft,the aerodynamic characteristics of the flexible deformed airfoil are investigated by using the Reynolds mean equation of incompressible fluid and the k-ωSST turbulence model on the simulation software.The aerodynamic characteristics of nine different deformation cases are compared and analyzed by comparing the flexible deflected airfoil with the conventional deflected airfoil and the flexible deflected airfoil itself.The results show that,compared with the conventional deflected airfoil,the lift-drag coefficients as well as lift-drag ratios of the flexible variable-deflection airfoil are different at the angle of attack-10°~7°.By analyzing the parameters of various flexible deformed airfoils,the effect law of three parameters,i.e.,rotating shaft position,deformation range and deflection angle,on the aerodynamic characteristics is concluded(i.e.,in order to obtain better lift-drag characteristics,the rotating shaft position with a small percentage of chord length,a small deflection angle,and a large deformation range should be selected as the angle of attack increases).
作者
孙新宇
段富海
SUN Xinyu;DUAN Fuhai(School of Mechanical Engineering,Dalian University of Technology,Dalian 116024,China)
出处
《飞行力学》
CSCD
北大核心
2023年第6期1-9,共9页
Flight Dynamics
基金
国家自然科学基金资助(51975082)。
关键词
后缘偏转
变弯度机翼
柔性变形机翼
气动特性
trailing edge deflection
variable camber wing
flexible morphing wing
aerodynamic characteristics
