变后掠角与变翼型厚度机翼的气动特性分析  

Analysis of aerodynamic characteristics of a wing with variable sweep angle and variable airfoil thickness

作　　者：冯文正 于菲[1] 姜涛 陈尚成 关玉明[1] FENG Wenzheng;YU Fei;JIANG Tao;CHEN Shangcheng;GUAN Yuming(School of Mechanical Engineering,Hebei University of Technology,Tianjin 300130,China)

机构地区：[1]河北工业大学机械工程学院,天津300130

出　　处：《飞行力学》2023年第1期9-13,共5页Flight Dynamics

摘　　要：为了探究变形翼的组合变形对于机翼气动特性的影响,首先,建立不同后掠角、翼型厚度的机翼模型;其次,对模型在宽广速域的扰流流场进行CFD数值模拟;最后,分析了在亚声速下机翼的升/阻力系数、升阻比、流场情况。研究结果表明:后掠角增大会减小升/阻力系数,但升阻比并非总是减小的趋势,速度越高,大后掠角越有优势;翼型厚度增大能够减缓大迎角下升阻比减小的趋势,对后掠角所引起的升阻比变化影响不大,当Ma=0.8时,机翼气动性能较差;同时考虑两者影响时,当Ma=0.8时,大后掠角、小翼型厚度具有较小的阻力系数和较高的升阻比,而小后掠角、大翼型厚度则更适合低亚声速飞行。In order to explore the influence of combined deformation on the aerodynamic characteristics of the wing, firstly, the wing model under different sweep angles, airfoil thicknesses was established;then, the CFD numerical simulation of the turbulent flow field in a wide speed domain was carried out on the model. Finally, the lift/drag coefficient, lift-drag ratio and flow field were analyzed at the subsonic flight speed. The research results show that the increase of the sweep angle will reduce the lift/drag coefficient. However, the lift-drag ratio does not always decrease. The large sweep angle will appear more advantage as the increasing of the speed. The increase of the airfoil thickness can slow down the decrease of the lift-drag ratio at a high angle of attack, which has little effect on the change of the lift-drag ratio caused by the sweep angle, and has a poor aerodynamic performance when Ma=0.8. When both influence are considered, the small airfoil thickness with a large sweep angle has a smaller drag coefficient and a higher lift-to-drag ratio when Ma=0.8, while the large airfoil thickness with a small sweep angle is more suitable for the low subsonic speed flight.

关 键 词：后掠角 翼型厚度 升阻比 流场结构 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]