翼根整流对串置式前掠翼气动特性影响研究

Research of the influence of wing root rectification on aerodynamic characteristics for a tandem forward-swept wing

为了综合发挥前掠翼和串置翼的气动力优势,提出一种串置高速前掠翼身组合基本模型,分别施加细边条和小填块以研究翼根整流影响。采用雷诺时均法和SST k-ω模型,对模型亚跨声速粘性流场进行数值仿真,分析纵向气动力特性和整流机理。结果表明:在来流马赫数0.8和迎角-5°～45°条件下,因前后翼气流相互作用,基本模型前翼升力系数大于后翼升力系数;前后翼翼根前同时加装小填块后,大迎角下模型翼根区域流动有所改善,但升阻特性变化不明显;加装边条后,翼根区域流动改善明显,迎角45°时模型最大升力系数提高了5.26%。

In order to fully utilize and enhance the aerodynamic advantages of forward-swept wing and tandem wing,a basic model with the fuselage combined with high-speed tandem forward-swept wing was proposed.Slender strake and small filling block are applied to study the influences of wing-root rectification.Reynolds time-averaged method and turbulence model are used to simulate transonic flow-fields of the model,and the longitudinal aerodynamic characteristics and rectifying mechanism are analyzed.Under the conditions of free-flow Mach number 0.8 and range of attack angles-5°to+45°,the results show that front wing lift coefficient of basic model is larger than that of the rear wing due to their mutual interaction.When the rectifying blocks are added to basic model,the wing-root zone flow is improved at high angles of attack,but the change of lift-drag characteristic is not obvious.After adding the strakes,flow improving effect of the wing-root zone is obvious,and maximum lift coefficient of the model increases by 5.26%at 45°angle of attack.