串置前掠翼模型亚音速升阻特性仿真

Simulation of Subsonic Lift-Drag Characteristics of the Tandem Forward Swept Wing Model

为探索挖掘前掠翼气动力优势,构建了一种串置式高速前掠翼布局研究模型,在来流马赫数0. 8和-10°～+20°中小攻角范围内,按RANS方法并选用可实现k-ε湍流模型,数值仿真其定常三维湍流场纵向气动力和受前后翼位置影响的变化特性。结果表明:在10°攻角后,串置式前掠翼基本模型获得的升力系数比相应单前掠翼的有所提高,而升阻比变化基本相同,串置翼基本模型在5°攻角时升阻比最大;在5°攻角之后,后翼下置串翼模型的升力系数比后翼上置和基本翼模型有所提高,而升阻比变化基本相同;在前后翼翼面附近绕流中捕捉到局部激波,并且翼根与机身交接区域可见有低速旋涡;串翼试飞模型平飞姿态稳定并能做一定机动飞行,串置式前掠翼模型构建方案可行,仿真计算为后续进一步开展研究奠定了基础。

In order to excavate the aerodynamic advantages of forward swept wing,a high-speed aerodynamic configuration model with tandem forward-swept wing was constructed.The aerodynamic forces of the models in the 3D viscous turbulent flow-field were numerically calculated by using RANS method and realizable k-εturbulence model in the free flow Mach number 0.8 and-10°to 20°of attack angles.The results show that the lift coefficient of basic model of tandem forward-swept wing is higher than those of the corresponding single forward-swept wing after 10 degree angle of attack,and the lift-drag ratio varies basically the same.The lift drag ratio of basic model of the tandem wing at 5 degree angle of attack is the largest.The lift coefficient of rear wing underlaying tandem wing model is higher than those of rear wing upper model and basic wing model after 5 degree angle of attack,but the lift-drag ratios are basically the same.Local shock waves were captured in the flow around the front and rear wing surfaces,and low-speed vortices were observed at the junction between the wing root and the fuselage.The attitude of the flight test model for the tandem wing was stable in horizontal flight and can also perform certain maneuvering flight.So the construction scheme of the tandem wing model is feasible,and the simulation lays a foundation for further carrying out relevant research.